Exercise validation study validation data, not blanket passes.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 20a091e52697f4e6ba2a913249fcee6cd97d0fe47d162f7bd04cd58b95c54af0
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Prescribed orientation, common filament dimensions and resin. Voigt stiffness averaging; not a manufacturing orientation prediction or progressive failure model. Thermal transport retains aligned closure assumptions.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: eea7cfba82a463af2fa7b2ce646587259661c887fedcbe354da53e4b4952bf0c
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Aligned monodisperse elastic fibers, perfect interface and concentric-cell shear lag. Halpin–Tsai transverse/shear screening closure. Existing constituent data are reused; the short-fiber composite and its strength allowables are a hypothetical teaching system.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 04ed0336b6be9695ad4e748292db996725a25b074241e2d0558859d7e58087e7
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Ideal continuous, aligned reinforcement with zero voids. This is a teaching comparison, not a measured material allowable.

Execution: Completed (not validation)

Nonzero-void closure has no matched published calibration in this study

Tested inputs

Input SHA-256: 11eaba020cf63d75fbcb86d94b5a264f56726e1f0fbf24bd56c3f8f65e5125e4
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Use the editable model inputs and their documented assumptions; matching a trend does not validate a strength prediction.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25}]

Input SHA-256: bcd87ea7ad5c3bc06958f1b2d1fadd0146279a7b20a56c59eb14e9ef46701135
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• ASTM-based teaching geometry, not certification. Grips, tabs, alignment and physical test validity are not simulated.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25}]

Input SHA-256: 27ead8b0d87202e94194ece226dc0c310644146bb20037a423cd5a1a31012421
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Small-strain elastic teaching model; fibre rotation and nonlinear termination rules are not represented.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.
• MIT / David Roylance — Beam Displacements ↗Equation 7, printed page 3: central-load simply supported beam. Euler–Bernoulli analytical check; excludes shear, contact, damage and empirical stiffness validation.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.5}]

{"widthMm":13,"heightMm":4,"spanMm":128,"forceN":100,"conditionalExGPa":51.92147387103631}

Input SHA-256: 91e88e45a71f71ba3943edfdefd2da46b3257da1978ea92d51c412986e39c8b8
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Procedure A teaching setup. Transverse shear deformation, roller contact and indentation are excluded.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.5}]

Input SHA-256: 2d861d978b4d1acddd9a15fcec68ec18937e735b0b6f32cc47e6d19fbe1ad8c9
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Procedure B teaching setup. Euler–Bernoulli bending excludes contact, indentation and shear deformation; the fixture is a setup visualization.

Execution: Completed (not validation)

Nonzero-void closure has no matched published calibration in this study

• MIT / David Roylance — Pressure Vessels ↗Equations 2–3, printed page 3; orthotropic strain compliance from laminated plates reference. Thin-wall, closed-end pristine cylinder. No slit, fracture or failure-pressure validation.
• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

{"pressureMPa":2.4,"externalPressureMPa":0,"innerRadiusMm":47,"wallMm":2,"closed":true,"axialNPerM":0}

Input SHA-256: 1de482a6e7dd14f5b66f5582d58c30b5f08af6a2b097f380ed49640e2fc60fc7
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Thin-wall membrane theory: no through-wall radial stress profile or local end effects.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 57c75183baed2b3f68a852fd744a42d57d40000fad29f111f797ae158bca1b56
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• One-dimensional through-thickness transport; lateral heat loss and oven airflow are not resolved. Inspect linked cure settings before interpreting reaction heating.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: bb7945add942903ef8b3ee0728f2c60f7009ca9fa28dd5bf469c3d4d60863170
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• One-dimensional Fickian transport with the selected constitutive inputs, not a prediction of chemical degradation.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: a5bbe55270ee23d8e37644d98072d548d60a62df8b3b7d774d9339417c62c42d
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Perfectly bonded linear-elastic interfaces. Mesh-sensitive edge peaks are not joint strength, debonding or damage predictions.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 09313577fe353090942f5be9e31eb875375255a460dec21dd0ccf19d699ffbd4
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Use the solver’s reported coupling state and limits. Do not assume this constitutes a general 3D coupled finite-element model or a calibrated cure-residual-stress prediction.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.
• MIT / David Roylance — Introduction to Composites ↗Equations 1–3, printed pages 3–4. Published analytical equations; not experimental material validation.

Tested inputs

[{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":45,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":0,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":-45,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":90,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":45,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":0,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":-45,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":90,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":90,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":-45,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":0,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":45,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":90,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":-45,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":0,"t":0.125},{"e1":105.3975,"e2":6.6707229456668165,"g":3.0535807494313425,"nu":0.28250000000000003,"angle":45,"t":0.125}]

Input SHA-256: cf30a05901ac5d8395b68239eba09463ab1835aa80aaf9b991760c78138b3a21
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Micro closure requires a separate published benchmark

Tested inputs

Input SHA-256: 1cc01f0305f88fe75e17664e8d989c68428bbee669fc16bc8891724193d1138f
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: f8073da725e399e78b9f1cc5e092c4736ab54adf82f7dc1e506adef932825d73
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 458f68015c6ea6569a6883328452399b9588f61284f3b33029fac443697b4f9b
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 6e19e98bad5bb57a271e72e93d74bdd68508a98b6d8a05e8df0b98bf1e342ce5
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: e0dc0b23396b81cebdbd5814b9d1a768de98afa847cc1c20cc1b994effa877ea
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 594ca160c9978dd99d1b636e8fd0c99edfd64818305e400797e1ad63b8466f80
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 9e7e0c49239516ec00c246c9db464639522e9134c519b4f505bc2d90cfc61277
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 3b570a1714db169929c1a14d44cfbdcd8e103086a3811ba868858e6dfba9a270
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 211d3bcf3313a256eaa4aa67203d043d414807f1b909bc934036760cd3974834
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: e11b26fab5c333c5d1d587e7dea556ecba8cad4485bedb88192f0e4c6477d2f0
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength. PA6/PET inputs are illustrative neat-matrix assumptions, not values taken from filled-filament coupons.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: c89c9c5ae5074c0889b249cd5fa7f2378fdfe90fa4bec945f009873908c11176
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength. PA6/PET inputs are illustrative neat-matrix assumptions, not values taken from filled-filament coupons.

Execution: Completed (not validation)

The copied T700/EP180 database is a connected starter, not T700/PR520. Complete the constituent setup below before comparing with NASA.

• NASA/TM—2015-218814 — Experimental and Numerical Analysis of Triaxially Braided Composites Utilizing a Modified Subcell Modeling Approach ↗Tables 3–4, printed page 7 / PDF page 11. MAC/GMC calculated effective ply data, not measured UD coupon properties.

Tested inputs

Input SHA-256: d17dbfeb419bab30b3a42e706d899f1198f976ab8cf816776095c2b8e773c02b
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Constituent-to-lamina screening only. The NASA braid subcells, calibrated LS-DYNA damage and coupon validation are not reproduced.

Source-matched constituent fixture compared with NASA MAC/GMC, 1% exploratory equivalence criterion declared before running. A different homogenization model need not match; mismatch is retained, not fitted away.

• NASA/TM—2015-218814 — Experimental and Numerical Analysis of Triaxially Braided Composites Utilizing a Modified Subcell Modeling Approach ↗Tables 3–4, printed page 7 / PDF page 11. MAC/GMC calculated effective ply data, not measured UD coupon properties.

{
  "fiber": {
    "E1": 230,
    "E2": 15,
    "G12": 27,
    "nu12": 0.2
  },
  "matrix": {
    "E": 4,
    "G": 1.44,
    "nu": 0.38
  },
  "volumeFractions": [
    0.375,
    0.733,
    0.8
  ],
  "voidFraction": 0,
  "model": "Rule of mixtures"
}

Source-matched constituent fixture compared with NASA MAC/GMC, 1% exploratory equivalence criterion declared before running. A different homogenization model need not match; mismatch is retained, not fitted away.

• NASA/TM—2015-218814 — Experimental and Numerical Analysis of Triaxially Braided Composites Utilizing a Modified Subcell Modeling Approach ↗Tables 3–4, printed page 7 / PDF page 11. MAC/GMC calculated effective ply data, not measured UD coupon properties.

{
  "fiber": {
    "E1": 230,
    "E2": 15,
    "G12": 27,
    "nu12": 0.2
  },
  "matrix": {
    "E": 4,
    "G": 1.44,
    "nu": 0.38
  },
  "volumeFractions": [
    0.375,
    0.733,
    0.8
  ],
  "voidFraction": 0,
  "model": "Halpin–Tsai model"
}

Execution: Completed (not validation)

The copied IM7 pressure-vessel records are scaffolding. Replace the ply source and dimensions with the published T700/epoxy inputs; a pressure load is not an axial or torsional test.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 8a21811556888bb0281f628c85a6e5ae7a20e4f3b4cdc4a3ad0c6c7961b6bca8
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Classical-laminate and first-ply screening. Manufacturing variation and qualification are excluded; the source describes estimated ply data.

Separate source-matched stiffness fixture, NOT the unchanged IM7 starter. Only Ex, Gxy and νxy. No experimental or strength validation.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

{
  "E1GPa": 153,
  "E2GPa": 10.5,
  "G12GPa": 8.27,
  "nu12": 0.3,
  "stack": "[45/-45]4",
  "thicknessMm": 2.345
}

Execution: Completed (not validation)

The starter resin and cycle are not TC380 calibration. The source supplies the schedule and measured checkpoints, but not all kinetics, heat-of-reaction or transport inputs. Source those inputs before a quantitative comparison.

• NASA — Evaluation of Temperature Gradients During Cure of a Thick Carbon Fiber/Epoxy Composite ↗Source study identified; quantitative reproduction not established. TC380 kinetics, reaction heat, transport, boundary characterization and digitized measurements still required.

Tested inputs

Input SHA-256: 243d2c53f31f339ed077611f011cd9145ea882b19843273b23e3857dbf102fe8
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• One-dimensional through-thickness study, not oven airflow or a general 3D process model. Missing TC380 calibration remains a setup requirement, never a default validated result.

Execution: Completed (not validation)

The starter uses IM7/8552, not AS4/3501-6. Supply traceable AS4/3501-6 ply properties, thickness and the source diameter convention before comparison. Slits are intentionally outside this pristine-cylinder model.

• NASA-CR-195101 — Damage Tolerance of Pressurized Graphite/Epoxy Tape Cylinders Under Uniaxial and Biaxial Loading ↗Source study identified; matched slit-cylinder dataset not reproduced. Slit-tip damage and failure pressure are outside pristine membrane scope.

Tested inputs

Input SHA-256: 5bbe273e59fe8c3cb1ccdad2ea589eae9805cee2808fbd97e62c1d1aa9e35a60
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Pristine-cylinder screening only. Slit-tip fracture, splitting, delamination, nonlinear local response and the source’s subcritical damage are not solved here.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 174f0e7506c6bad11e871d07431e70faffa754645a1ecf39db3674b99097309e
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative constant-speed T700/epoxy process. Uniform face-fed, through-thickness Darcy infusion uses prescribed Kz, a continuous resin manifold and local ply-average cure viscosity; pressure or total flow controls the inlet and pump limits are reported. Fixed equivalent-composite thermal properties; no dry-to-wet feedback, resin heat advection, axial flow, leakage, die thermal mass or pulling-force prediction. Not a calibrated production recipe.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: d1ea4ba532980733b74afb6167ec3363897e4eec1ed6b5cdee7621f75cc91b97
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative constant-speed T700/epoxy process. Uniform face-fed, through-thickness Darcy infusion uses prescribed Kz, a continuous resin manifold and local ply-average cure viscosity; pressure or total flow controls the inlet and pump limits are reported. Fixed equivalent-composite thermal properties; no dry-to-wet feedback, resin heat advection, axial flow, leakage, die thermal mass or pulling-force prediction. Not a calibrated production recipe.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 4daf0ee9fbf98bb8340e4e700aa2403d279496fd1b02236fe33c99db6cbf85c5
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Hypothetical UV-compatible teaching composite: inherited T700/epoxy elastic and transport values do not establish commercial resin UV compatibility or carbon-composite transparency. Effective optics, kinetics and enthalpy require calibration. No oxygen transport, shadowing, multiple scattering or radical dark cure. Use Run, not UV process optimization.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: eb9401d8110813c940db288452a02f7f6275df23792f462c59faa29cfcc30478
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative linear-sorption diffusion only. Skin D=1e−12 m²/s, saturation=1.5%, dry density=1900 kg/m³; balsa D=1e−10 m²/s, saturation=30%, dry density=150 kg/m³. No capillary flow, salt transport, defects, edge ingress, degradation or service-life validation. Swelling coefficients are explicitly zero: stress/warpage predictions are not part of this exercise. Elastic properties are placeholders for the shared laminate workflow.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 74e47beeac04d25b167a2a8346fabeae9e519ddc5d89e53b5404f74578889a67
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Ideal continuous, aligned reinforcement with zero voids. This is a teaching comparison, not a measured material allowable.

Execution: Completed (not validation)

Nonzero-void closure has no matched published calibration in this study

Tested inputs

Input SHA-256: a468ff89a6e21a4051d545095967733716371a607ff7f9d3e7fddadc3727684f
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Use the editable model inputs and their documented assumptions; matching a trend does not validate a strength prediction.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 29ed22b08119e3fc813cb99c1c6f82bb0a92e899679b2ce24a128fb1fbbc643d
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Aligned monodisperse elastic fibers, perfect interface and concentric-cell shear lag. Halpin–Tsai transverse/shear screening closure. Existing constituent data are reused; the short-fiber composite and its strength allowables are a hypothetical teaching system.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 0e48d2e0ce48b6b6d582193529400ed6df726a76b9439fcb7614caf217a38615
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Prescribed orientation, common filament dimensions and resin. Voigt stiffness averaging; not a manufacturing orientation prediction or progressive failure model. Thermal transport retains aligned closure assumptions.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25}]

Input SHA-256: b2d69654216cd27cfaf4c152ecc24d05e533df0b6339a7c67e01cd322aafc3ca
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• ASTM-based teaching geometry, not certification. Grips, tabs, alignment and physical test validity are not simulated.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25}]

Input SHA-256: 1fcaf524be3985112116b47fb710cfde3c7ff23a4a334764b519f0522ea23684
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Small-strain elastic teaching model; fibre rotation and nonlinear termination rules are not represented.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.125},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.125}]

Input SHA-256: 015ceedf6b728e402320b125e211e272f42bbe134430f6d599c690ca208367ea
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored representative lamina properties, not a solved Micro recipe or qualified design allowables.

Execution: Completed (not validation)

Nonzero-void closure has no matched published calibration in this study

Tested inputs

Input SHA-256: 1b598c4267668d24407a42a4c7d01b140b7a6a5bba1b17e5c0021e4e8821e4eb
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Reference-state elastic laminate comparison; different ply sources and thicknesses are intentional. Representative properties are not qualified allowables.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.
• MIT / David Roylance — Beam Displacements ↗Equation 7, printed page 3: central-load simply supported beam. Euler–Bernoulli analytical check; excludes shear, contact, damage and empirical stiffness validation.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.5},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.5}]

{"widthMm":13,"heightMm":4,"spanMm":128,"forceN":100,"conditionalExGPa":51.92147387103631}

Input SHA-256: 6ad7bc35c5fcb1ae7f19264bfe2555c203c064f8d34f6c8c69d45131afa6cc87
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Procedure A teaching setup. Transverse shear deformation, roller contact and indentation are excluded.

Execution: Completed (not validation)

Nonzero-void closure has no matched published calibration in this study

• MIT / David Roylance — Pressure Vessels ↗Equations 2–3, printed page 3; orthotropic strain compliance from laminated plates reference. Thin-wall, closed-end pristine cylinder. No slit, fracture or failure-pressure validation.
• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

{"pressureMPa":2.4,"externalPressureMPa":0,"innerRadiusMm":47,"wallMm":2,"closed":true,"axialNPerM":0}

Input SHA-256: 1705b0def02c615b6d74adc554ab50b1f48e4277213cf89d3951ee86bae2a9aa
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Thin-wall membrane theory: no through-wall radial stress profile or local end effects.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 88ffe99546b4db167f8f04ccaed2aafd9c290c3ce91ded5ec244fb6ac0127813
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Perfectly bonded linear-elastic interfaces. Mesh-sensitive edge peaks are not joint strength, debonding or damage predictions.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 3ea686aa2ca0e25b50aaff7bab097b5cb2a3211e5d575a59e5d0b348de9ab1e9
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative strengths only. Local peel and mixed-mode bond growth are not assessed. Completion is not an overall sandwich pass.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 0c5609e0d06a3cae73e9605b0809afcba1a57b8fdd1276b3bee1e7598a334eca
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• One-dimensional through-thickness transport; lateral heat loss and oven airflow are not resolved. Inspect linked cure settings before interpreting reaction heating.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: c31dceba88870cf26839a9c1de2e26298849ec1fd928b2635f068ed829167cc0
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• One-dimensional Fickian transport with the selected constitutive inputs, not a prediction of chemical degradation.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 1a26511d799dadd4fda98042e06d460c90323d616567fb201edaac993ca1b4ac
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative constant-speed T700/epoxy process. Uniform face-fed, through-thickness Darcy infusion uses prescribed Kz, a continuous resin manifold and local ply-average cure viscosity; pressure or total flow controls the inlet and pump limits are reported. Fixed equivalent-composite thermal properties; no dry-to-wet feedback, resin heat advection, axial flow, leakage, die thermal mass or pulling-force prediction. Not a calibrated production recipe.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 4edb4b943ca8e46d379ba7501033a536287f6f342959f056a7c23ca2aeda5386
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Hypothetical UV-compatible teaching composite: inherited T700/epoxy elastic and transport values do not establish commercial resin UV compatibility or carbon-composite transparency. Effective optics, kinetics and enthalpy require calibration. No oxygen transport, shadowing, multiple scattering or radical dark cure. Use Run, not UV process optimization.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 9c2ebe8e1209f14d084e9188ac98c6a91ebe67a50f0f4aff13b8d17b54078678
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Use the solver’s reported coupling state and limits. Do not assume this constitutes a general 3D coupled finite-element model or a calibrated cure-residual-stress prediction.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 5b50c095a1854dad43e675564265034cc86f6affb6b98fcf02e62a54571df3ff
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Use the solver’s reported coupling state and limits. Do not assume this constitutes a general 3D coupled finite-element model or a calibrated cure-residual-stress prediction.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 339e24fbd1335f484e0ac5f308a47a499bab3b17aae85581dd184c8c82fde77a
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Use the solver’s reported coupling state and limits. Do not assume this constitutes a general 3D coupled finite-element model or a calibrated cure-residual-stress prediction.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 286962496a3a7b275986109ca0849755f9c196705dacef795f0c1474854c636f
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Mechanical-only x-z reference-state demonstration coupling cohesive interfaces and in-plane ply damage. No thermal/moisture residual loading, out-of-plane ply failure or full 3D validation. Assumed teaching strengths and fracture energies; never a design certification.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125}]

Input SHA-256: 8d9431bae7d9ecc2b654b1015748f669c95645d2c981d93576129d3d2743b4bd
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125}]

Input SHA-256: 7ed9b921322c87822c64cc51e68813fde11ca243b7266fb7d924d998262da9b6
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":0,"t":0.135}]

Input SHA-256: f2c52e207df87954f90a95a09544d887a76cd308c5f8bb9958cbac8e3d7c4a81
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":0,"t":0.13999999999999999}]

Input SHA-256: 66e164c7634705c806cbea280e8673d01828bc4dc588afb8692c67f2b7e3d9f4
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125}]

Input SHA-256: 031e3c74177fba796323029d1604301cc3fd56a27666f8b54d1c50d9f2f77dd1
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":45,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":-45,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":90,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":90,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":-45,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":45,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125}]

Input SHA-256: 2ad63134874ab22f166d5eb80068af1404936f54714e7e7db1f674182c6c77a2
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":0,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":45,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":-45,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":90,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":90,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":-45,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":45,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":0,"t":0.135}]

Input SHA-256: 464dcb2550dc24117533463e4eaffec72a35f422004efb0d92e490e28bc7c300
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":0,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":45,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":-45,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":90,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":90,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":-45,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":45,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":0,"t":0.13999999999999999}]

Input SHA-256: fb6349be1950a7743172b3cbd0729fb087792558a48d639fa4d97dea61da4527
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":90,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":90,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":45,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":-45,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":0,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":0,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":-45,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":45,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":90,"t":0.135},{"e1":172,"e2":9.8,"nu":0.31,"g":5.6000000000000005,"angle":90,"t":0.135}]

Input SHA-256: 96e673c499fdbb035287f252435eca914fe9623ecc86c6d98b1fbc8f1600635d
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":132,"e2":8.4,"nu":0.31,"g":4.5,"angle":0,"t":0.125}]

Input SHA-256: eaddf1f4c0c80f1a08cb453412e6056eb8160a3ff0f1281a8f7bcbf56380078d
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":174,"e2":9.4,"nu":0.31,"g":5.300000000000001,"angle":0,"t":0.125}]

Input SHA-256: 876ab69c0f64590cd2a87cf67b5abd0a8e4a7e6cdd2aa81bab61af7d51cfe126
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":137,"e2":8.9,"nu":0.31,"g":4.9,"angle":0,"t":0.12999999999999998}]

Input SHA-256: 162abfefb99eb1cac123b41b76d09073c36ce530564013bd9f871aee06ab4a85
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":62.00000000000001,"e2":62.00000000000001,"nu":0.08,"g":4.2,"angle":0,"t":0.22}]

Input SHA-256: 05b5eff410549859048f3f3e79e4adec6147f4c5ad6e427938213089af8276da
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125}]

Input SHA-256: 55189b04ae330bdc8d1e8812c5d17c20cc8ab92d277f5e9c1454e53dce7e9453
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125}]

Input SHA-256: 2a0e2ea575b3151c69d110975d2075e6fa91782b23e9b5128639d64cc040e9b6
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125}]

Input SHA-256: c9b97c5e5f5997246fe2eb21e672eb9105e9c7a90898ca40eaef7c2e4f58e5c7
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":0,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":90,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":0,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":90,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":90,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":0,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":90,"t":0.13999999999999999},{"e1":142,"e2":10,"nu":0.3,"g":5.5,"angle":0,"t":0.13999999999999999}]

Input SHA-256: 1be78838e180dfa4cd62ab46a31eb1e925682be58d14c2507f1afa167bd4e997
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":62.00000000000001,"e2":62.00000000000001,"nu":0.08,"g":4.2,"angle":0,"t":0.22},{"e1":62.00000000000001,"e2":62.00000000000001,"nu":0.08,"g":4.2,"angle":45,"t":0.22},{"e1":62.00000000000001,"e2":62.00000000000001,"nu":0.08,"g":4.2,"angle":-45,"t":0.22},{"e1":62.00000000000001,"e2":62.00000000000001,"nu":0.08,"g":4.2,"angle":90,"t":0.22},{"e1":62.00000000000001,"e2":62.00000000000001,"nu":0.08,"g":4.2,"angle":90,"t":0.22},{"e1":62.00000000000001,"e2":62.00000000000001,"nu":0.08,"g":4.2,"angle":-45,"t":0.22},{"e1":62.00000000000001,"e2":62.00000000000001,"nu":0.08,"g":4.2,"angle":45,"t":0.22},{"e1":62.00000000000001,"e2":62.00000000000001,"nu":0.08,"g":4.2,"angle":0,"t":0.22}]

Input SHA-256: fb4baf1ca769edff4dd859778c90ad1bcb302b909f226461143a00fc1dfb659e
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":132,"e2":8.4,"nu":0.31,"g":4.5,"angle":0,"t":0.125},{"e1":132,"e2":8.4,"nu":0.31,"g":4.5,"angle":45,"t":0.125},{"e1":132,"e2":8.4,"nu":0.31,"g":4.5,"angle":-45,"t":0.125},{"e1":132,"e2":8.4,"nu":0.31,"g":4.5,"angle":90,"t":0.125},{"e1":132,"e2":8.4,"nu":0.31,"g":4.5,"angle":90,"t":0.125},{"e1":132,"e2":8.4,"nu":0.31,"g":4.5,"angle":-45,"t":0.125},{"e1":132,"e2":8.4,"nu":0.31,"g":4.5,"angle":45,"t":0.125},{"e1":132,"e2":8.4,"nu":0.31,"g":4.5,"angle":0,"t":0.125}]

Input SHA-256: d182977994748171e1a0baa7fd0058ab5ad68f919ddf311e5d8ec283082d948a
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":174,"e2":9.4,"nu":0.31,"g":5.300000000000001,"angle":0,"t":0.125},{"e1":174,"e2":9.4,"nu":0.31,"g":5.300000000000001,"angle":45,"t":0.125},{"e1":174,"e2":9.4,"nu":0.31,"g":5.300000000000001,"angle":-45,"t":0.125},{"e1":174,"e2":9.4,"nu":0.31,"g":5.300000000000001,"angle":90,"t":0.125},{"e1":174,"e2":9.4,"nu":0.31,"g":5.300000000000001,"angle":90,"t":0.125},{"e1":174,"e2":9.4,"nu":0.31,"g":5.300000000000001,"angle":-45,"t":0.125},{"e1":174,"e2":9.4,"nu":0.31,"g":5.300000000000001,"angle":45,"t":0.125},{"e1":174,"e2":9.4,"nu":0.31,"g":5.300000000000001,"angle":0,"t":0.125}]

Input SHA-256: 73b653e654263c65b6509ce1964619f45c13a8b1b416f8c03724162329b04a3e
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":137,"e2":8.9,"nu":0.31,"g":4.9,"angle":0,"t":0.12999999999999998},{"e1":137,"e2":8.9,"nu":0.31,"g":4.9,"angle":45,"t":0.12999999999999998},{"e1":137,"e2":8.9,"nu":0.31,"g":4.9,"angle":-45,"t":0.12999999999999998},{"e1":137,"e2":8.9,"nu":0.31,"g":4.9,"angle":90,"t":0.12999999999999998},{"e1":137,"e2":8.9,"nu":0.31,"g":4.9,"angle":90,"t":0.12999999999999998},{"e1":137,"e2":8.9,"nu":0.31,"g":4.9,"angle":-45,"t":0.12999999999999998},{"e1":137,"e2":8.9,"nu":0.31,"g":4.9,"angle":45,"t":0.12999999999999998},{"e1":137,"e2":8.9,"nu":0.31,"g":4.9,"angle":0,"t":0.12999999999999998}]

Input SHA-256: a00f5b4b6822f73a3bc298257414eae813a108ee4d90fc61d7daffff6181d585
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":45,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":-45,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":90,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":90,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":-45,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":45,"t":0.125},{"e1":165,"e2":9,"nu":0.32,"g":5.2,"angle":0,"t":0.125}]

Input SHA-256: 5e427e9159257d5c7e817f64545b5ef42a27ab07ef7464d9b4047babffac5737
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125}]

Input SHA-256: 08903bf6c1fe816959ce21a6a6a829c0add1ee68c7770be19e3f4bd91d04895b
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":90,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":0,"t":0.125}]

Input SHA-256: c05708848156e0188cfd67b36fb9c17fa3ceaf9e3d4dbdff1f548cec75603b6c
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":-45,"t":0.125},{"e1":134,"e2":8.8,"nu":0.31,"g":4.800000000000001,"angle":45,"t":0.125}]

Input SHA-256: 141472aa6defbbf46c320e2d65f5bc17b83d2ae66d007e0611b6c2d4a8788541
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Stored original ply properties; original homogenization and failure-model selections are not rerun. Maximum-stress screening uses original teaching strengths, not qualified allowables. Linear CLT resultants only: no grip/edge boundary layers, buckling, delamination, progressive growth or process coupling. Completion is not validation or a physical pass.

Execution: Completed (not validation)

FSDT module regression checks cover independent analytical plate solutions and refinement. This particular exercise has not received a full quantitative benchmark badge; do not inherit a CLT-only pass for its FSDT fields.

Tested inputs

Input SHA-256: 47f721a36e498cb0203df585c1f7e6ff9f5eb3b6ee65a8a2c63b1bee735d2044
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Reference-elastic symmetric rectangular FSDT plate. Idealized teaching data, no calibrated material/strength claim. No thermal/moisture preload, thickness stretch, contact, debonding, damage or postbuckling. Directional energy-equivalent shear correction is an approximation; refine numerical order and compare published solutions.

Execution: Completed (not validation)

FSDT module regression checks cover independent analytical plate solutions and refinement. This particular exercise has not received a full quantitative benchmark badge; do not inherit a CLT-only pass for its FSDT fields.

Tested inputs

Input SHA-256: 94a4b543fba4d7b28a36bcd0128c82ce704f32eae75508a87b1f01ed9ea03bcd
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Reference-elastic symmetric rectangular FSDT plate. Idealized teaching data, no calibrated material/strength claim. No thermal/moisture preload, thickness stretch, contact, debonding, damage or postbuckling. Directional energy-equivalent shear correction is an approximation; refine numerical order and compare published solutions.

Execution: Completed (not validation)

FSDT module regression checks cover independent analytical plate solutions and refinement. This particular exercise has not received a full quantitative benchmark badge; do not inherit a CLT-only pass for its FSDT fields.

Tested inputs

Input SHA-256: 0276b8fbdbcf7b23e255cb77a5f2435be71cd5be4f2cd9194aa2813c91fc9ce1
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Reference-elastic symmetric rectangular FSDT plate. Idealized teaching data, no calibrated material/strength claim. No thermal/moisture preload, thickness stretch, contact, debonding, damage or postbuckling. Directional energy-equivalent shear correction is an approximation; refine numerical order and compare published solutions.

Execution: Completed (not validation)

FSDT module regression checks cover independent analytical plate solutions and refinement. This particular exercise has not received a full quantitative benchmark badge; do not inherit a CLT-only pass for its FSDT fields.

Tested inputs

Input SHA-256: d9c11adb809514d14201a78001aa5bf7d18142f62fb287ecf811207898a1719c
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Reference-elastic symmetric rectangular FSDT plate. Idealized teaching data, no calibrated material/strength claim. No thermal/moisture preload, thickness stretch, contact, debonding, damage or postbuckling. Directional energy-equivalent shear correction is an approximation; refine numerical order and compare published solutions.

Execution: Completed (not validation)

FSDT module regression checks cover independent analytical plate solutions and refinement. This particular exercise has not received a full quantitative benchmark badge; do not inherit a CLT-only pass for its FSDT fields.

Tested inputs

Input SHA-256: 976a0c9020a0dfc0a18163c97ce8ecd63f2799547c465a33348a2ba64c9cbb52
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Reference-elastic symmetric rectangular FSDT plate. Idealized teaching data, no calibrated material/strength claim. No thermal/moisture preload, thickness stretch, contact, debonding, damage or postbuckling. Directional energy-equivalent shear correction is an approximation; refine numerical order and compare published solutions.

Execution: Completed (not validation)

FSDT module regression checks cover independent analytical plate solutions and refinement. This particular exercise has not received a full quantitative benchmark badge; do not inherit a CLT-only pass for its FSDT fields.

Tested inputs

Input SHA-256: c0a31ae8e052c5ad520237728c5b29a96e22a3180ae8910aec90fba696b5e04e
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Reference-elastic symmetric rectangular FSDT plate. Idealized teaching data, no calibrated material/strength claim. No thermal/moisture preload, thickness stretch, contact, debonding, damage or postbuckling. Directional energy-equivalent shear correction is an approximation; refine numerical order and compare published solutions.

Execution: Completed (not validation)

Editable teaching assembly: 6 mm bolt, 36 mm plate width, 14 mm washer. Linked laminate supplies thickness and extensional stiffness. Retained pretension is a force, not a torque.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 13e4e58cd72ef2ccf7d569144f5c39d28fd66052dafb817344ca72f8a0c1aaf0
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Single-fastener monotonic elastic stick, Coulomb slip and clearance-bearing law with independent measured bearing, net-section, shear-out, clamp-compression and bolt-shear limits. Uniform washer pressure; no 3D contact or progressive ultimate failure. ASTM D5961 is a method reference; teaching setup is not a compliance claim.

Execution: Completed (not validation)

Editable teaching assembly: 6 mm bolt, 36 mm plate width, 14 mm washer. Linked laminate supplies thickness and extensional stiffness. Retained pretension is a force, not a torque.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: ec67d5719a4bb88634d2d51801e283e06b185567601549fd30d1006f539d9d52
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• CDS variational finite-difference membrane model, unilateral spring pin and prescribed annular friction. Separately superposed uniform washer compression is not a 3D solution. The cited clamping paper motivates model limits; CDS does not reproduce its 3D progressive-damage formulation.

Execution: Completed (not validation)

Editable teaching assembly: 6 mm bolt, 36 mm plate width, 14 mm washer. Linked laminate supplies thickness and extensional stiffness. Retained pretension is a force, not a torque.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: ee4668dca6601c4ab6cdcf1eee6771b9f20228e66c2af0fc6df1b99f00e7fdc3
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Equal adherends with adhesive shear-lag, one or two clearance/friction/bearing connectors, closed-form Green-function or finite-difference solution. Shared displacement determines load sharing. No hybrid peel, prying, adhesive plasticity, crack growth or progressive ultimate strength.

Execution: Completed (not validation)

30-ply symmetric cross-ply T700 teaching specimen, 150 × 100 × 3.75 mm; 125 × 75 mm support window and 16 mm nose. Review ASTM, calibration and model limits.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: d5ec6a4a813373b0fe33bd6c8163c57b4437536ed39472ec1396c29923ff1b22
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• First plate mode with CLT bending stiffness and Hertz elastic contact. Symmetric specially orthotropic thin plate, center strike, supplied density and indentation coefficient. Force, displacement and energy histories; higher modes, membrane stiffening, permanent indentation and damage are excluded. ASTM D7136 is a method reference, not a compliance claim.

Execution: Completed (not validation)

30-ply symmetric cross-ply T700 teaching specimen, 150 × 100 × 3.75 mm; 125 × 75 mm support window and 16 mm nose. Review ASTM, calibration and model limits.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 6624eed10e2b8c4ca134528fabf75d86906f296a48defc3d8a90b2f00072f337
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Two-mass Hertz contact with irreversible calibrated scalar plate stiffness loss and explicit energy accounting. Supplied damage coefficients are illustrative until measured calibration. No damaged area, failure-mode map, penetration or residual CAI strength is predicted.

Execution: Completed (not validation)

30-ply symmetric cross-ply T700 teaching specimen, 150 × 100 × 3.75 mm; 125 × 75 mm support window and 16 mm nose. Review ASTM, calibration and model limits.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 4bdf220cdb7d48a5530310c37b54beb18a34d45196a2c659ec6a0774dfcec6e0
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Elastic CLT first-mode plate compliance plus Hertz indentation. Symmetric specially orthotropic thin plate and supplied contact coefficient. Total displacement is plate deflection plus contact indentation. Fixture compliance, permanent indentation and damage propagation are excluded.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: f289f06620b6b2a648e2ed1d30d14b7ca25d1a96a062007b50ef75d7453eaa56
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Uniform small-strain compression using linked laminate Ex and thickness. Measured compressive strength supplies a screening ratio; fixture, tabs, buckling and failure evolution are not simulated.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 4e3da1510dd995f23e7d72887c5197b8662069bd05d78de5424d22dc6cc157b6
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Uniform nominal shear between notches using linked laminate Gxy and thickness. Not a notch/fixture stress field or nonlinear shear solution. Gauge length is the effective shear deformation length, not crosshead travel.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: bf35b77d5bac49822250fe955001b160a8039c4a2ced46561f97ca45f791501d
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Ideal Euler–Bernoulli DCB with equal homogeneous 0° arms, each half the linked laminate thickness. No root rotation, shear, large displacement or cohesive growth. Critical load is an initiation estimate from supplied GIc.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: cbb14733bf614529a12881255a6e5810dd5e7e57c3f6dc317d15c3cb43825ea4
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Ideal equal-arm, homogeneous 0° ENF beam; support span is twice the half-span. Crack must be shorter than the half-span. No shear/root correction or unstable crack growth. GIIc is supplied, not fitted automatically.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 433c63e34872b53d6371dd2b98113e4bafcb9c226a29cdd8912ffd7afe057d20
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Benzeggagh–Kenane envelope from calibrated GIc, GIIc and exponent. Supplied GI/GII are energy-release rates from a separate test reduction or analysis. This does not resolve the MMB lever fixture or propagate a crack.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 70079cef78401e7c9e567bee2ee2869788c5f9f491383ce718a4ea4466049d17
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Homogeneous slab, initially dry, both faces held at equilibrium moisture. Fits diffusivity from two early uptake measurements (both ≤50% saturation) using the square-root-time approximation. Edge ingress and temperature dependence are excluded. Does not overwrite material properties.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: d6b4cc5c90badd96321e8fea8591488bec35c73ad94ab0537d85a9fb8c6a5389
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Single-pin nominal bearing, net-section and shear-out checks with independent measured allowables. Bypass tension is added to net-section load only. No contact, bolt preload, load redistribution or validated bearing–bypass interaction envelope.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 6e61899dee675b5d0a9f80d2c05d8526d23e65bd26be919a35e916213abf50f4
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Nominal gross/net stress and demand relative to measured open-hole compressive strength for this geometry and layup. This is test-data screening, not an uncalibrated notch-strength prediction. No local buckling or kink-band simulation.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 0c19a95741ff913fa51514fc196ccc26ed51c42b846c65bdea9bc8bc650e4ae7
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Compares user-measured open- and filled-hole compressive strengths using gross-section stress. Use matched layup, hole, environment and fastener condition. Filling a hole does not automatically recover strength; no fastener contact/preload model is applied.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 2bfe4df47f67f1d4f0a8b49d4dca72edd5102448936534579cb169a0118fe7b2
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Incident energy from measured impact velocity; residual compressive strength from measured peak CAI force. Rebound energy estimates energy not returned to the striker, NOT damage energy. No impact/contact solver, damage-area prediction or energy-to-strength extrapolation.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 40cc38c041d23d39fbbf1322cd2050f3716e278fb82738a5df6686d6881e1774
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Gross/net nominal tension and demand relative to measured open-hole tensile strength for the same geometry and layup. No uncalibrated notch-strength prediction, local hole stress or damage evolution.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 5de13d6558e3c9d12d8c1bb1416aca4badc310583c4b258db1078eef0fe686b1
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Constant-amplitude Basquin S–N interpolation using stress AMPLITUDE, calibrated at one exact tensile R ratio. Coefficients and limits are hypothetical defaults: replace them and document the measured source/environment in Parameter basis. No damage growth, scatter, self-heating or extrapolated life.

Execution: Completed (not validation)

A 32-ply, 8 mm laminate with a circular bonded specimen. Enter measured through-thickness properties; in-plane modulus is not substituted.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 4cfbe1cff702422c979c121da660dfed86f2ca23d273ba2450d075426179ab93
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Circular coupon loaded normal to its plane through bonded thick metal end-tabs. Uniform stress uses actual circular area, supplied through-thickness Ez and linked stack thickness. In-plane E2 is not Ez. Block/bond restraint and interlaminar failure evolution are excluded.

Execution: Completed (not validation)

Bare PVC core: one 20 mm layer. Enter measured directional core properties and allowables in the test case.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 570d89d68fb0b97d19c2b01fdfc7f93d346ae2d9a02cd017c7cb438ba26c1a1f
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Bare-core nominal shear between bonded loading plates. Stress is force / bonded plan area; shear strain uses explicit core G and relative plate displacement across linked core thickness. Use a core-only stack. End effects, adhesive slip and cell-scale fields are excluded.

Execution: Completed (not validation)

Bare PVC core: one 20 mm layer. Enter measured directional core properties and allowables in the test case.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: f2708cd30d4bffa72dd652d1f3b886c8f613aea675950dc31f7ade4c07809fbe
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Uniform flatwise compression of a core-only stack between platens. Supplied core Ez gives elastic strain and shortening. Nominal stress uses the full plan area including cells. No crush plateau, densification, platen friction or automatic 2%-deflection strength inference.

Execution: Completed (not validation)

Two 1 mm T700 facesheets around a 20 mm PVC core. Test-direction properties and strengths are explicit illustrative inputs.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: d3c6bdc4dec87eaba9567c8a55f24ed0c14f3a71f5850fbc750608c2ce754e7f
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Uniform flatwise tension of equal-faced sandwich bonded to loading blocks. Compare nominal stress with independent measured core, bond and facesheet through-thickness strengths. Explicit Ez values give series compliance; bondline/block compliance is neglected. Core + two faces must equal linked stack thickness.

Execution: Completed (not validation)

Two 1 mm T700 facesheets around a 20 mm PVC core. Test-direction properties and strengths are explicit illustrative inputs.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: b5df85c436d34ad0b2f942eafc10d2b1622316a4390118a1f2f59ffa4b1f8eff
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Symmetric three-point sandwich nominal core shear and mean facesheet stress from actual core/face dimensions. Equal thin faces, negligible axial core load. Core + two faces must match linked stack. Screening only: no indentation, wrinkling, debond growth or predicted displacement.

Execution: Completed (not validation)

Two 1 mm T700 facesheets around a 20 mm PVC core. Test-direction properties and strengths are explicit illustrative inputs.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: f39f3a0c95c47ff6eed71531bdca14383dc85c883c46a2e59ef11385c4ee2963
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Symmetric four-point long-beam sandwich with equal thin faces and support span/total thickness >20. Nominal face/core stress plus ideal elastic midspan displacement from supplied face Ex and core G. Ignores axial core stiffness, indentation, wrinkling, adhesive compliance and damage. Not a D7250 stiffness reduction.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 702633b93c4a0ba64b3304b26ca32ddbaf82de85a764c9c66b6cd32c2901e7cd
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Positive lossless dielectric bounds; complex directional estimates. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 484fc58fbdd4a28bf75b60b60267d1ea4b00de10e601e85a5004ec65e9862d1b
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• One cube-root mixing law, not two independent models. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: b126c6323402544a008e025f6bb982dfd748934a23ea15f1331748f6a6926012
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Dilute subwavelength spherical inclusions in a host. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 605c3f9b4ebf342ea6c5a44785888467952f48f50ee2c9bab8193deac7e2f6db
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Coherent isotropic nonmagnetic layers between air half-spaces. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 7c2f44e639a310ecdda78e7b3a70bf0117909f0637aa7fd212d2065096ac2e9d
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Two positive-permittivity phases; no explicit contact network. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 00732e420b90895aac4ce7a62861069d5d4261e803771fb3760ec0d1ccdc1f8a
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Scalar principal-axis ellipsoidal field approximation. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 65cb60496cd8a72e58aeb74857b492abf021ea26c4a5fc49611792ac90b90692
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Scalar principal-axis self-consistency; spherical case equals Bruggeman. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: bcc95d4a03355f58b214e978753031745776f6ed95c731dfe717b05f3e516c29
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Incremental mixing with time-step refinement check. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 3807066d4bf8fc572754a827cd6eaaae0613c226bbecfec95f35e4d3ee98dee9
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Concentric subwavelength coated spheres; no dynamic Mie scattering. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 5dec6225f861330d394b4ae77f3ecaa75931ee3fc3963cb51bc52e34b835e3b3
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Spherical multiphase Bruggeman with convergence checks. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: cb78d85366aee41b4e2cf7b396c5331553a3259f64f6488f250dddd0363a0a4b
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• TE or TM waves; scalar isotropic layers, no polarization conversion. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 0ce314d4b0806141ecf6addc57ecd883b336e4c6158155e1ce6b2c1f1247963b
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Normal-incidence lossless delay-line mesh with pulse decay, energy and mesh-refinement safeguards. Explicit Run required; not a 3D solver. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Explicit dielectric teaching inputs. Mechanical laminate properties are not used in this separate RF study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 6abd81c613f780b3a079be46c3b4f0c0b16258ef22ad77afb247f400c1b700f5
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Lossless isotropic A/B unit-cell eigenvalues, folded Bloch phase and stop-band attenuation at normal incidence. Not arbitrary-cell homogenization. Positive-permittivity, passive, nonmagnetic RF screening only. This separate study uses explicit EM inputs, not mechanical or cure properties. Illustrative defaults are not measured T700 properties.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 71969656f4d5e25daf753fc4a6018b82eec6fd33550e7707e5601b6bc3a711f4
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Infinite-width, specially orthotropic tension screening. Point and average stress distances must be calibrated independently for this laminate. Not compression, bearing or a joint allowable.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 9c67c86cf8f1f8a8ae19893cb3e794b233cbea63e055b85580d114f6963c57dc
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Linear uniaxial response at the calibration temperature. Reference Ex is the instantaneous modulus. Three Maxwell branches; creep is solved from stress equilibrium, not the reciprocal relaxation modulus. No thermal shifting or nonlinear creep.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 1084ba85c44a22e10df52a0d006119e55580d94901b3df2b0021907b3952b6b3
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Identical equivalent-elastic adherends, long free arms and a thin elastic adhesive. Compare shear-only Volkersen with eccentric single-lap shear and peel. Not a debonding, plasticity or strength calculation.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 0694d61656d103949da1e533f4b258254dc73360766d6194b3a49ad404e532ce
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• NASA LaRC04 linear-shear specialization, evaluated at both faces of every ply under membrane and bending loads. Supplied ply strengths are effective/in-situ values; no automatic thin-ply enhancement. Initiation only, not degradation or nonlinear-shear instability.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: fd41c8344dba8f88c581cd5f61dc8af1b038dfb932e4f538972a28f875e95f00
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Free CLT release from prescribed ply-local shrinkage/thermal eigenstrains. Corner spring-in is a separate uniform-strain estimate. Stress-free temperature and effective post-gel shrinkage need calibration. No tool friction, cure kinetics or viscoelastic restraint history.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: fda5c67e1685907b0f5e5c604fa3ec79f2889076eb63fb469f97f8ece611860d
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Prescribed power-law retention fitted to constant-amplitude tests at a fixed stress ratio, amplitude and temperature. Stiffness and strength have independent coefficients. S–N life alone cannot calibrate either. Does not modify the saved laminate.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: e1d0c42ed873d002d53487399bab77a6434bea431ec85070f091dfc8c7dd2db3
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Simply supported, thin, specially orthotropic cylinder under uniform axial compression. Discrete Donnell modes; prescribed knockdown factor explores imperfection sensitivity, not a prediction from measured imperfection amplitude. No pressure, torsion, postbuckling or strength pass.

Execution: Completed (not validation)

Illustrative calibration only. Start with a 16-ply cross-ply reference laminate; this is a separate, reference-state study.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 116ada98e88388bde6ff7f3d344515e2a44860b24dd1573f76416558685afe15
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Seeded independent uniform sampling of shared modulus, ply-thickness and angle offsets. Recomputes laminate ABD for each sample. Bounds are assumptions, not measured distributions. Percentiles and sensitivity are exploratory, not reliability certification.

Execution: Completed (not validation)

Face-clamped rail fixture with a wider gauge section. Dimensions are editable teaching inputs; verify the current standard and actual fixture before physical testing.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: a2f717cfe8463016f251c9aaa8cb9cad875938e1ba26a7078c0560001383fa1d
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Uniform nominal shear between notches using linked laminate Gxy and thickness. Not a notch/fixture stress field or nonlinear shear solution. Gauge length is the effective shear deformation length, not crosshead travel.

Execution: Completed (not validation)

Editable teaching assembly: 6 mm bolt, 36 mm plate width, 14 mm washer. Linked laminate supplies thickness and extensional stiffness. Retained pretension is a force, not a torque.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 8b307c67925c1ac743f5a6d025222d124bb458c7d5cc224dfdde491140360808
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Single-fastener monotonic elastic stick, Coulomb slip and clearance-bearing law with independent measured bearing, net-section, shear-out, clamp-compression and bolt-shear limits. Uniform washer pressure; no 3D contact or progressive ultimate failure. ASTM D5961 is a method reference; teaching setup is not a compliance claim.

Execution: Completed (not validation)

Editable teaching assembly: 6 mm bolt, 36 mm plate width, 14 mm washer. Linked laminate supplies thickness and extensional stiffness. Retained pretension is a force, not a torque.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 7146098798de03099f8600eaf096fc4791437920d25cc2422e8cd96bcd7dceb2
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Equal adherends with adhesive shear-lag, one or two clearance/friction/bearing connectors, closed-form Green-function or finite-difference solution. Shared displacement determines load sharing. No hybrid peel, prying, adhesive plasticity, crack growth or progressive ultimate strength.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 0a2518c1c0a35abc42c23b23077c78adfee02296e52a86309b1d9a22cb2bd5eb
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Guided optimization case study using shared database records. Configure the documented search in Optimize, then save its results and inputs. No precomputed optimum or benchmark-validation claim. Ideal continuous, aligned reinforcement with zero voids. This is a teaching comparison, not a measured material allowable.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25}]

Input SHA-256: c11a1f2102c96d12956d63360d1d53f3c9ed0aa0d1a51b6e2fee1325aaca93b7
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Guided optimization case study using shared database records. Configure the documented search in Optimize, then save its results and inputs. No precomputed optimum or benchmark-validation claim. ASTM-based teaching geometry, not certification. Grips, tabs, alignment and physical test validity are not simulated.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: b3f90096f41118d36138a85cbca62e3cb714cd86d9e8c144c74929c324aec1ca
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Guided optimization case study using shared database records. Configure the documented search in Optimize, then save its results and inputs. No precomputed optimum or benchmark-validation claim. One-dimensional through-thickness transport; lateral heat loss and oven airflow are not resolved. Inspect linked cure settings before interpreting reaction heating.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 10d1e7eef2a7fb52c448a4ef5556211a12662b3870f233f9ac66364af82c4748
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching inputs, not qualified allowables. Sequential coupling transfers the reported thermal/moisture state to laminate mechanics; it is not simultaneous 3D multiphysics. Inspect the transferred state and reference values before interpreting stress or curvature.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 30ae77f9c1fab2e4cd3db9b1ae050fa78c5afd8d651926c423c02e6f53eff63c
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching inputs, not qualified allowables. Sequential coupling transfers the reported thermal/moisture state to laminate mechanics; it is not simultaneous 3D multiphysics. Inspect the transferred state and reference values before interpreting stress or curvature. Free laminate CLT curvature, not fixture-constrained distortion, a full tool-release simulation or calibrated cure-shrinkage prediction.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: e110ab3cc6485e17ef28b606a522da974859b268ea507869e686c087637ed951
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching inputs, not qualified allowables. Sequential coupling transfers the reported thermal/moisture state to laminate mechanics; it is not simultaneous 3D multiphysics. Inspect the transferred state and reference values before interpreting stress or curvature. No moisture-driven damage, swelling-dependent diffusion or experimentally calibrated strength degradation.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: c6555bca94985a202bcdbdaed1d0439c4bd7e2a5467abb5b8e3ecc03b16c96c2
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative constant-speed T700/epoxy process. Uniform face-fed, through-thickness Darcy infusion uses prescribed Kz, a continuous resin manifold and local ply-average cure viscosity; pressure or total flow controls the inlet and pump limits are reported. Fixed equivalent-composite thermal properties; no dry-to-wet feedback, resin heat advection, axial flow, leakage, die thermal mass or pulling-force prediction. Not a calibrated production recipe. Sequential outlet-state structural screening under a prescribed resultant; no pulling force, die friction, impregnation or load feedback into the thermal solution.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 96e5f90b98c4ae60eb42a46bf99e633e76285bd021ccb1be607a06905b1ce093
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Hypothetical UV-compatible composite; effective optics, kinetics, shrinkage and modulus require calibration. Carbon/epoxy source data do not prove UV transparency or compatibility. CLT includes thermal and post-gel chemical-shrinkage stress; distinguish peak stress from the cooled residual state. No fixtures, tool contact, oxygen transport, radical dark cure or viscoelastic relaxation. Not manufacturing validation.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: b23bcf9e7219e675dd4638e311446bb98230413503de0ee1b40f189ea88e8cab
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Hypothetical UV-compatible composite; effective optics, kinetics, shrinkage and modulus require calibration. Carbon/epoxy source data do not prove UV transparency or compatibility. CLT includes thermal and post-gel chemical-shrinkage stress; distinguish peak stress from the cooled residual state. No fixtures, tool contact, oxygen transport, radical dark cure or viscoelastic relaxation. Not manufacturing validation.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 030c43f0d19c0174bb0882cd0dca97bbaddbab295d329a5f807759b1959119f7
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Hypothetical UV-compatible composite; effective optics, kinetics, shrinkage and modulus require calibration. Carbon/epoxy source data do not prove UV transparency or compatibility. CLT includes thermal and post-gel chemical-shrinkage stress; distinguish peak stress from the cooled residual state. No fixtures, tool contact, oxygen transport, radical dark cure or viscoelastic relaxation. Not manufacturing validation.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: b175d00fa2fc1e73861a417df3e27e57f966d74afe0b8c05000055d79b4bce15
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Hypothetical UV-compatible composite; effective optics, kinetics, shrinkage and modulus require calibration. Carbon/epoxy source data do not prove UV transparency or compatibility. CLT includes thermal and post-gel chemical-shrinkage stress; distinguish peak stress from the cooled residual state. No fixtures, tool contact, oxygen transport, radical dark cure or viscoelastic relaxation. Not manufacturing validation.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 35d88ab3d7c32782b7126bf8017bdeda929cbe5342d2d34884a65366befae086
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative constant-speed T700/epoxy process. Uniform face-fed, through-thickness Darcy infusion uses prescribed Kz, a continuous resin manifold and local ply-average cure viscosity; pressure or total flow controls the inlet and pump limits are reported. Fixed equivalent-composite thermal properties; no dry-to-wet feedback, resin heat advection, axial flow, leakage, die thermal mass or pulling-force prediction. Not a calibrated production recipe. Sequential outlet-state structural screening under a prescribed resultant; no pulling force, die friction, impregnation or load feedback into the thermal solution.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: ad74312f1dd0cf464e7604e6e6ca46b63886851fea1a1afe1bef0fe74251b516
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative constant-speed T700/epoxy process. Uniform face-fed, through-thickness Darcy infusion uses prescribed Kz, a continuous resin manifold and local ply-average cure viscosity; pressure or total flow controls the inlet and pump limits are reported. Fixed equivalent-composite thermal properties; no dry-to-wet feedback, resin heat advection, axial flow, leakage, die thermal mass or pulling-force prediction. Not a calibrated production recipe. Sequential outlet-state structural screening under a prescribed resultant; no pulling force, die friction, impregnation or load feedback into the thermal solution.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: a07178f48ebf394ec82827a6497448ee6337c00ea8f65ab26a89c27eaf980bbf
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching inputs, not qualified allowables. Sequential coupling transfers the reported thermal/moisture state to laminate mechanics; it is not simultaneous 3D multiphysics. Inspect the transferred state and reference values before interpreting stress or curvature.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 87854c11b46ce8726e95b5415b7bc9d18fbba10a75e60ca6f4f32e6b2f00548b
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching inputs, not qualified allowables. Sequential coupling transfers the reported thermal/moisture state to laminate mechanics; it is not simultaneous 3D multiphysics. Inspect the transferred state and reference values before interpreting stress or curvature. Free laminate CLT curvature, not fixture-constrained distortion, a full tool-release simulation or calibrated cure-shrinkage prediction.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 6e80e0580934eec26fef36cf8b6e197feda3e1acb357546531615b6055554e98
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching inputs, not qualified allowables. Sequential coupling transfers the reported thermal/moisture state to laminate mechanics; it is not simultaneous 3D multiphysics. Inspect the transferred state and reference values before interpreting stress or curvature. No moisture-driven damage, swelling-dependent diffusion or experimentally calibrated strength degradation.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 28a4afa38a53e905eba79c827a6ce51b7638f0792cc479b6801620647ba2a20e
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching inputs, not qualified allowables. Sequential coupling transfers the reported thermal/moisture state to laminate mechanics; it is not simultaneous 3D multiphysics. Inspect the transferred state and reference values before interpreting stress or curvature. Free laminate CLT curvature, not fixture-constrained distortion, a full tool-release simulation or calibrated cure-shrinkage prediction.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: c3e78791f966bfcd53a5453ed116b9501a038762e10ce351269bed8de296d22c
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative oven schedules and convection coefficients using teaching laminate and cure data. One-dimensional thickness transport; no oven airflow, radiation exchange, tooling thermal mass or equipment control model. Calibrate material kinetics and boundary conditions before manufacturing use.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 0dd101a2c0a638c208111043b8d2c7a0d22726dc3c9c2825eaf58dcfad1a216e
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative oven schedules and convection coefficients using teaching laminate and cure data. One-dimensional thickness transport; no oven airflow, radiation exchange, tooling thermal mass or equipment control model. Calibrate material kinetics and boundary conditions before manufacturing use.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 2fdfbfebc305b39a21981539acdeb33197c197085c078f911656eaaa5fcaf3a7
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative oven schedules and convection coefficients using teaching laminate and cure data. One-dimensional thickness transport; no oven airflow, radiation exchange, tooling thermal mass or equipment control model. Calibrate material kinetics and boundary conditions before manufacturing use.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: dab61518f21c2de1f7fdd4fadf12916eae38d80a5c682dc98af496609a4305ec
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative elastic screening, not measured material data or strength prediction. Prescribed axial/planar orientation mixture with stiffness-domain averaging, perfect interface and monodisperse fibers. Transverse and shear closure is approximate. Zero strength inputs mean failure is not assessed.

Execution: Completed (not validation)

Nonzero-void closure has no matched published calibration in this study

Tested inputs

Input SHA-256: 98a2fd8f744c7458ff6a6b4f68eecd3105758091977262ba09835c6618bc3da8
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 6ec99fab92792ab51a994b2743a291e357f7acb847b637fd31ff0883286ab5fc
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Teaching-only constituent/architecture assumptions. Elastic screening; no qualification, processing prediction or measured composite strength.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25}]

Input SHA-256: 2568cd6245725469be44ef85751e20e34cf204c26dc4b276e239b2315d2f1aa0
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Guided optimization case study using shared database records. Configure the documented search in Optimize, then save its results and inputs. No precomputed optimum or benchmark-validation claim. ASTM-based teaching geometry, not certification. Grips, tabs, alignment and physical test validity are not simulated.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.25},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.25}]

Input SHA-256: bd08ad57cd4fe8599ae9fb4c4a350e1100a50ce6781d7761361bd0f08822ef44
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Guided optimization case study using shared database records. Configure the documented search in Optimize, then save its results and inputs. No precomputed optimum or benchmark-validation claim. ASTM-based teaching geometry, not certification. Grips, tabs, alignment and physical test validity are not simulated.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 2a96555b149f44128461b2aedb821c14b54cf281abbcfe130e4bcb37fb3101d6
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative elastic screening, not measured material data or strength prediction. Prescribed axial/planar orientation mixture with stiffness-domain averaging, perfect interface and monodisperse fibers. Transverse and shear closure is approximate. Zero strength inputs mean failure is not assessed.

Execution: Completed (not validation)

User-reported operating data supply approximately 10% Average duty cycle for each 2 kW lamp and 40% for the 1620 W long and 1080 W short plates. Review the Hardware values, then Run. The 290°F controller senses chamber air; plate surface temperature remains a prescribed model assumption. All four roller surfaces are prescribed at 240°F, 50°F below the oven, as a sensitivity assumption. No saved predictions are supplied.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: afd250eb71dbecdbcd898a589a9a3102c0272dd8c4aac0412cc77d101fa6edfe
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative production-process exercise, not a validated recipe. The approximate user-reported operating data do not validate predicted heat transfer. Mean plate electrical consumption does not determine heat delivered to the web; the existing 143.333333°C plate surface temperature remains a prescribed assumption. The averaging model does not simulate controller cycling or chamber-air dynamics. Initial 30 Shore A rubber constants use a hardness correlation, not hot-rubber calibration. Resin kinetics, permeability, radiant conversion, absorptance and contact parameters need characterization. Fixed equivalent plies omit resin enthalpy advection, axial flow and thickness compaction.

Execution: Completed (not validation)

User-reported operating data supply approximately 10% Average duty cycle for each 2 kW lamp and 40% for the 1620 W long and 1080 W short plates. Review the Hardware values, then Run. The 290°F controller senses chamber air; plate surface temperature remains a prescribed model assumption. All four roller surfaces are prescribed at 240°F, 50°F below the oven, as a sensitivity assumption. No saved predictions are supplied.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 1882ae216cfef781e9660b0818a0dc0b799b168f02677e467fe205e711efd5cf
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative production-process exercise, not a validated recipe. The approximate user-reported operating data do not validate predicted heat transfer. Mean plate electrical consumption does not determine heat delivered to the web; the existing 143.333333°C plate surface temperature remains a prescribed assumption. The averaging model does not simulate controller cycling or chamber-air dynamics. Initial 30 Shore A rubber constants use a hardness correlation, not hot-rubber calibration. Resin kinetics, permeability, radiant conversion, absorptance and contact parameters need characterization. Fixed equivalent plies omit resin enthalpy advection, axial flow and thickness compaction.

Execution: Completed (not validation)

User-reported operating data supply approximately 10% Average duty cycle for each 2 kW lamp and 40% for the 1620 W long and 1080 W short plates. Review the Hardware values, then Run. The 290°F controller senses chamber air; plate surface temperature remains a prescribed model assumption. All four roller surfaces are prescribed at 240°F, 50°F below the oven, as a sensitivity assumption. No saved predictions are supplied. Three physical layers resolve 0.22 mm epoxy / 1.00 mm dry core / 0.22 mm epoxy. Fiber and supplied resin inventory match the original feedstock recipe; the 1.44 mm physical domain differs from its 1 mm equivalent thermal approximation.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 1512f4808c277f15e60bd241c1d2ed2c6422ef8d890d6f728fa1db7009fe500f
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative production-process exercise, not a validated recipe. The approximate user-reported operating data do not validate predicted heat transfer. Mean plate electrical consumption does not determine heat delivered to the web; the existing 143.333333°C plate surface temperature remains a prescribed assumption. The averaging model does not simulate controller cycling or chamber-air dynamics. Initial 30 Shore A rubber constants use a hardness correlation, not hot-rubber calibration. Resin kinetics, permeability, radiant conversion, absorptance and contact parameters need characterization. Fixed resin/core/resin geometry preserves the initial physical feedstock ledger; resin enthalpy advection, moving film depletion, changing heat capacity, axial flow and thickness compaction are omitted. Numerical thermal contact or fill predictions are not experimental validation.

Execution: Completed (not validation)

User-reported operating data supply approximately 10% Average duty cycle for each 2 kW lamp and 40% for the 1620 W long and 1080 W short plates. Review the Hardware values, then Run. The 290°F controller senses chamber air; plate surface temperature remains a prescribed model assumption. All four roller surfaces are prescribed at 240°F, 50°F below the oven, as a sensitivity assumption. No saved predictions are supplied. Three physical layers resolve 0.22 mm epoxy / 1.00 mm dry core / 0.22 mm epoxy. Fiber and supplied resin inventory match the original feedstock recipe; the 1.44 mm physical domain differs from its 1 mm equivalent thermal approximation.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: f17d1e5ade8e93cb78ae12f7829f2c4ae52b2738baf3c9e78396245ee9d118ed
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative production-process exercise, not a validated recipe. The approximate user-reported operating data do not validate predicted heat transfer. Mean plate electrical consumption does not determine heat delivered to the web; the existing 143.333333°C plate surface temperature remains a prescribed assumption. The averaging model does not simulate controller cycling or chamber-air dynamics. Initial 30 Shore A rubber constants use a hardness correlation, not hot-rubber calibration. Resin kinetics, permeability, radiant conversion, absorptance and contact parameters need characterization. Fixed resin/core/resin geometry preserves the initial physical feedstock ledger; resin enthalpy advection, moving film depletion, changing heat capacity, axial flow and thickness compaction are omitted. Numerical thermal contact or fill predictions are not experimental validation.

Execution: Completed (not validation)

Editable numerical candidate: 6 heated nip pairs (two rollers per pair). 500 lbf per pair is one shared closing force. Run to calculate current temperature, infusion and film screening; no frozen predictions are bundled.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: bf88e67f61132819884f1469427513b073a70baefd45b1ac7ddcdfa9d368ac79
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Fixed-geometry 1D thermal/infusion and one-way longitudinal film screening. No enthalpy advection, compaction, transverse wrinkles, torque/speed feedback or qualified hot film allowables. Enclosure and frame clearances require mechanical review.

Execution: Completed (not validation)

Editable numerical candidate: 8 heated nip pairs (two rollers per pair). 500 lbf per pair is one shared closing force. Run to calculate current temperature, infusion and film screening; no frozen predictions are bundled.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: dda8272209cbcd26219e9ace6d7214282d20bc413255c05c5920b2fabd0950bd
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Fixed-geometry 1D thermal/infusion and one-way longitudinal film screening. No enthalpy advection, compaction, transverse wrinkles, torque/speed feedback or qualified hot film allowables. Enclosure and frame clearances require mechanical review.

Execution: Completed (not validation)

Independent copy of P.02.11. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 8 films supply 3.008 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: f1482fb70b8ae59d3871d7d0c2b765a387ec0ad975e9c5347e7158d16610e37e
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Surrogate paper inputs. Independent copy of P.02.11. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 8 films supply 3.008 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

Execution: Completed (not validation)

Independent copy of P.02.12. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 8 films supply 3.008 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 7147cf435e25dbf1478ec839fb3ca0f6acde9a90a2109f53a3aeb5d76d355c9c
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Surrogate paper inputs. Independent copy of P.02.12. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 8 films supply 3.008 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

Execution: Completed (not validation)

Independent copy of P.02.13. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 2 films supply 0.752 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 59cf6ee178ffd2023c6ef6e0b7d09256cd930c942288b52acb78191f65f0d831
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Surrogate paper inputs. Independent copy of P.02.13. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 2 films supply 0.752 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

Execution: Completed (not validation)

Independent copy of P.02.14. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 2 films supply 0.752 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 8ef1fda66bfbdfd8cc22566d78241e7b3cee0f0273f40e86608facfc4dca2fdd
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Surrogate paper inputs. Independent copy of P.02.14. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 2 films supply 0.752 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

Execution: Completed (not validation)

Independent copy of P.02.15. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 2 films supply 0.752 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: 2708227022873c863bf6124b8c5900c47cdf0af57d7f0f03f48d1c1de96999bf
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Surrogate paper inputs. Independent copy of P.02.15. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 2 films supply 0.752 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

Execution: Completed (not validation)

Independent copy of P.02.16. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 2 films supply 0.752 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

• NASA/TM—2014-216635 — Engineered Polymer Composites Through Electrospun Nanofiber Coating of Fiber Tows ↗Tables 1–2, printed pages 11–12 / PDF pages 15–16. Published estimated ply inputs and CLPT tube properties, not qualified or experimentally validated strengths.

Tested inputs

Input SHA-256: c492bb4a5bd35749b2ff43b820a882df18b85a9c8e39e9cc9f4c0cdce0c6ddee
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Surrogate paper inputs. Independent copy of P.02.16. Resin thickness is user-confirmed 376 micrometers PER film. Both exterior paper layers are editable thermal materials. All thermal geometry, film supply and porous-bed positions come from the laminate. The 2 films supply 0.752 mm resin equivalent; this is not inventory-matched to the two-skin stack. Paper properties are surrogates, not measurements.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 351cfc292c084dafb658303432980dd786bbff9ef4e6e7a385652d294ba06d2a
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Explicitly synthetic scalar dielectric properties at 2.45 GHz, representative PEI thermal inputs, planar normal incidence and through-thickness heat flow. No cavity resonance, lateral temperature field or electrical-temperature feedback.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 60533d758265e81d1579fa4f20f5b0d256a01ff80a51852ef60ac51ae3be9665
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative AS4/PEEK material and power calibration with existing contact/healing reference coefficients. Fixed geometry and thermal properties exclude latent heat, crystallization and degradation; pressure is prescribed. No material deposition, joint deformation, metal/polymer adhesion or qualified weld strength is predicted.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 472c3175dcbc06eb0e0e1839bff65a7c25a52573c2775ed39c08337698b3c3e3
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative AS4/PEEK material and power calibration with existing contact/healing reference coefficients. Fixed geometry and thermal properties exclude latent heat, crystallization and degradation; pressure is prescribed. No material deposition, joint deformation, metal/polymer adhesion or qualified weld strength is predicted.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 711f613e88a11ace84305c0ac1bce186e41bbee2e630e79634299544c982d75d
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Synthetic geometry/current/conductivity/efficiency and existing PEEK contact/healing/crystallization teaching coefficients. Independent isotropic thin sheets omit electrical contacts between plies, reaction fields, magnetic cores, hysteresis, coil circuits and lateral temperature. Approximation guards are conservative screening limits, not validated error bounds or a structural weld qualification.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: fcacd16f20f221c227ce48c7a6a5a598233430ae7a9f2b4c09c060104b956aab
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative neat PEI bead and previously deposited PEI substrate. Reuses the default RES-017 PEI / ULTEM representative starter card unchanged; its constant reference thermal values are not calibrated melt-state or grade-specific data. The melt exit is prescribed at 350°C. No melting/crystallization latent heat, nozzle internal flow, bead spreading, molecular healing or weld strength is predicted.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 51749d9133b92aabb45833d234af6590407f5a04598111aa47c39e2a18513517
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative neat PEEK local through-thickness build, not a full raster/toolpath or printer calibration. The unchanged RES-014 family card supplies constant reference thermal properties. Independent copies of the existing AS4/PEEK contact/healing coefficients are teaching assumptions for this neat-PEEK example, not a vendor-grade weld characterization. Initial contact is explicitly assumed to be 60%; no pressure-driven consolidation, self-weight, capillary neck growth, nozzle compaction, void removal or qualified strength is inferred. This example uses stationary chamber/bed anneal holds without extrusion or head heating.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: e7a670fda7ccae94e37ba44c553def9d2e72d2c71f23ee48f1f45b8183ec6b92
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative neat PEI local through-thickness build on a two-layer substrate, followed by two head reheating passes. Uses the unchanged RES-017 PEI / ULTEM family starter card and its constant reference thermal properties; these are not grade-specific melt-state measurements or a printer calibration. The melt exit is prescribed at 350°C and the head wall at 380°C. The local head supplies a finite heat-transfer exposure, not laser irradiation. No raster path, whole-part heat accumulation, nozzle flow, bead spreading, pressure-driven contact, molecular healing, crystallization, degradation or weld strength is predicted.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: c576a7635fde5dc68636c4a6fa9c3a7c96eace60a9a035aeede7bb24efd10b54
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative PA12-family thermal teaching study, not a supplier grade, calibrated powder recipe or production qualification. Dense density 1010 kg/m³, specific heat 1700 J/kg·K and dense conductivity 0.25 W/m·K are explicit teaching assumptions. Powder packing, conductivity, optical absorption, melting interval, latent heat and viscosity/surface tension are separately entered illustrative process values. Replace these with measurements for the selected powder and laser wavelength. The existing Arkema PA12 grade card is not modified or represented as this powder. Fixed mass and mesh with a peak-liquid-fraction conductivity proxy; no densification, shrinkage, recoating, resolved melt velocity, crystallization kinetics or mechanical strength is predicted.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 2de9823c0bbb1073959b04323be483e755afddd4456070205bf2275c918006c7
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative PA12-family thermal teaching study, not a supplier grade, calibrated powder recipe or production qualification. Dense density 1010 kg/m³, specific heat 1700 J/kg·K and dense conductivity 0.25 W/m·K are explicit teaching assumptions. Powder packing, conductivity, optical absorption, melting interval, latent heat and viscosity/surface tension are separately entered illustrative process values. Replace these with measurements for the selected powder and laser wavelength. The existing Arkema PA12 grade card is not modified or represented as this powder. Fixed mass and mesh with a peak-liquid-fraction conductivity proxy; no densification, shrinkage, recoating, resolved melt velocity, crystallization kinetics or mechanical strength is predicted.

Execution: Completed (not validation)

A coupled, damage, transport or local-field comparison needs matched constitutive data, boundary conditions and field/mesh convergence. Execution alone is insufficient.

Tested inputs

Input SHA-256: 4279a1fcd198910d31a9f590943adc7a777404b7b91de98ebbfe9776c5fd0d9b
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Illustrative PA12-family thermal teaching study, not a supplier grade, calibrated powder recipe or production qualification. Dense density 1010 kg/m³, specific heat 1700 J/kg·K and dense conductivity 0.25 W/m·K are explicit teaching assumptions. Powder packing, conductivity, optical absorption, melting interval, latent heat and viscosity/surface tension are separately entered illustrative process values. Replace these with measurements for the selected powder and laser wavelength. The existing Arkema PA12 grade card is not modified or represented as this powder. Fixed mass and mesh with a peak-liquid-fraction conductivity proxy; no densification, shrinkage, recoating, resolved melt velocity, crystallization kinetics or mechanical strength is predicted.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":210,"e2":210,"nu":0.3,"g":80,"angle":0,"t":3}]

Input SHA-256: b81dcaf9be6a34d2f22a5a17572392dadca2163555e09c18aef12fbc821eace9
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Linear elasticity only. No plastic strain, necking, metal fracture, fatigue or composite ply-discount damage is predicted. Published yield is a reference limit for the elastic display, not a fitted stress-strain curve. Fixture compliance, grip slip and alignment are excluded. ASTM references identify related physical methods; the uniform rectangular idealization is not a complete compliant E8/E8M test.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.

Tested inputs

[{"e1":69,"e2":69,"nu":0.33,"g":25.939849624060148,"angle":0,"t":3}]

Input SHA-256: efb0167432089dffa3b03de0cca084a5df00f80c369b1c1fb3cb0572c3f30710
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Linear elasticity only. No plastic strain, necking, metal fracture, fatigue or composite ply-discount damage is predicted. Published yield is a reference limit for the elastic display, not a fitted stress-strain curve. Fixture compliance, grip slip and alignment are excluded. ASTM references identify related physical methods; the uniform rectangular idealization is not a complete compliant E8/E8M test.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.
• MIT / David Roylance — Beam Displacements ↗Equation 7, printed page 3: central-load simply supported beam. Euler–Bernoulli analytical check; excludes shear, contact, damage and empirical stiffness validation.

Tested inputs

[{"e1":210,"e2":210,"nu":0.3,"g":80,"angle":0,"t":3}]

{"widthMm":20,"heightMm":3,"spanMm":128,"forceN":50,"conditionalExGPa":210.00000000000003}

Input SHA-256: 5a5889b1fee9e6838e5313427a8a4cefd738cf3a0c350723af1a479ab6811242
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Linear elasticity only. No plastic strain, necking, metal fracture, fatigue or composite ply-discount damage is predicted. Published yield is a reference limit for the elastic display, not a fitted stress-strain curve. Fixture compliance, grip slip and alignment are excluded. No E290 bend-ductility or plastic-hinge solution is supplied.

Execution: Completed (not validation)

• MIT / David Roylance — Laminated Composite Plates ↗Transformed plane-stress constitutive law and laminate extensional stiffness, equations 10–11 and 20–25. Independent strain/stress transformation and thickness integration; prescribed input elasticity is not validated.
• MIT / David Roylance — Beam Displacements ↗Equation 7, printed page 3: central-load simply supported beam. Euler–Bernoulli analytical check; excludes shear, contact, damage and empirical stiffness validation.

Tested inputs

[{"e1":69,"e2":69,"nu":0.33,"g":25.939849624060148,"angle":0,"t":3}]

{"widthMm":20,"heightMm":3,"spanMm":128,"forceN":50,"conditionalExGPa":69.00000000000001}

Input SHA-256: a79d4e2dbcf26af7c34cb7e6ddd3093ebfe2d4e6a5e58a9d8db5d975d3d109f7
Solver source SHA-256: cde316d69ee40b2714f26fd4d6d822f774242b37323c9419f2b6142aff317ca9

• Linear elasticity only. No plastic strain, necking, metal fracture, fatigue or composite ply-discount damage is predicted. Published yield is a reference limit for the elastic display, not a fitted stress-strain curve. Fixture compliance, grip slip and alignment are excluded. No E290 bend-ductility or plastic-hinge solution is supplied.