Exercise validation study
evidence, not blanket passes.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 023d0f9e37fe6991aec84fc5d1e767b154474fe12c72baa7c0cf2f5d0c86aafd
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 73613037a84dd9d81b7c835830d0126c51fc8a9220398c8d68196c12bb7eb4ca
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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)

• 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":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125}]

Input SHA-256: 33568bf12395e4ef96259f641b50c3640ee6c9b360aa0ef5e4d14898130dbb28
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 7efdac50f52ddf75e8b4238c482ab15921472e1407e11540098592f2bbea4d69
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 836db69b310704dde69f38ec94a84e77804e11fe6bf3a83d72c92adbb7c5f2fe
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 5dd1c8c280e7a6d810c16958a148ce9612bee00ec4ef64d667e1fd12a1b6ee79
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: cfff30037077572d8a78930111a6075d1e7bd289386fac40761bc5ba23b44289
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: d715756d3c42db7eaf95f301006df8a3bd758480ee32595c9bac8d07a425542d
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 87a70c6801176c35b7c43b7879038a694b53331c161031294165e7c41b8a31a1
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: b71ca4ae14043d00eda72575be629e5bae7c2130a472aaa44ea481327600fcbd
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 4cc786e3fdb263fb815b47a3fa847bca58cc4cc9445b9a959352657db64a9e36
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 0d720826073bcc480c3a0839f8689ce52e5fecc77ce6012fedd5041833821559
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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)

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: f332a9c41bf7dc1aaa5eb2521be80c1e6feeef085db48ea61d81a3475b42b7b9
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 8a86a623acc8d1dbf229bcb467cc07faef12e797aff844c6cc071a5fa1cb8be4
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: bf765b769c16e22bd102d6e21b2eabccdfbb0052ff58ca608a19c3e6bd41f127
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: f25f2006b61b91faeeba0759fa4d7a801d98047fe892d401285db11b9d1b9741
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 309a118972d336406bb87064a0c4b29667775455a9a263ca556e1f4898d6bacc
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• Hypothetical teaching process using existing T700/epoxy laminate properties and illustrative cure parameters, not a calibrated pultrusion recipe. Constant-speed moving section; no axial conduction, impregnation, leakage, die thermal mass or pulling-force prediction. Use Thermal Run, not batch-cycle 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: d55be911e277f7f1bd7a9fe626df2e00715f1ed1bebd953926e61a8289643a9f
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• Hypothetical teaching process using existing T700/epoxy laminate properties and illustrative cure parameters, not a calibrated pultrusion recipe. Constant-speed moving section; no axial conduction, impregnation, leakage, die thermal mass or pulling-force prediction. Use Thermal Run, not batch-cycle 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: 17ff6a467903997fbcf273aa11d1b5673e5cbe9f6ade2d15c7d48c3042eb8665
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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)

• 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":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125}]

Input SHA-256: aa8dfddc57c6603f78995bb5ff5e8797e25120e6c516522eb1527869b3c2db5f
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: fe8a5d925d7a9672a29a01937edd9eb3c2b42e9bc990465914b779757874a18b
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: d46c9d65a01da0589efb0b1f0f2f2879417418c728dcff023e4e8f92676e2498
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 3f4298967362cc557933886740e660ff04460efaa4c684506056e7697709a547
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 31c790afc826dbb5f4074293cc8b84fbeb2ae8fca2643602d20f876e486b0b58
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: cd753353f468747f32fb5ce841c98a92862751f1676e8ed64b174dc8117141c3
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 716863f81d436bdb736f6a540eaadea8c3b9f6250e027a030e0577b90c3a3729
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• Stored representative lamina properties, not a solved Micro recipe or qualified design 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 — Introduction to Composites ↗Equations 1–3, printed pages 3–4. Published analytical equations; not experimental material validation.

Tested inputs

[{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.1},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.15},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.1},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.15},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.1},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":0,"t":0.15},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.1},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":90,"t":0.15},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.1},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.15},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.1},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.15},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.1},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":-45,"t":0.15},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.1},{"e1":135,"e2":9,"nu":0.31,"g":4.8,"angle":45,"t":0.15}]

Input SHA-256: ed0977222c5537dcedc599a3781853426a39092fe7348bc62af909840e65b6fb
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: d1c6f8d713ec3b367de695d459b61a6e248b08652742fb4dda8c8a63b1585100
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 4c78b03f4d4b30abe5f0ed42092b43e1f3ad98337f59993b06b31530007b28d8
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 2dc19ff14fb7dd8fd4f66fe7e1118256a2a9c03fe290bb786071deab9bf2c8ff
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: b0c086a36d3c83659cf60f767b9688a1c0e9c3184651b43afb46a1d11033245b
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: d6b08a2f7e79b272f9195def9722072a73f6d6f3b478257bc6e66e02050c6817
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: c0e20c31f83d2ee767259d3686c99bd5b08438139add36a995b35c824663bb05
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 4c9e7eddd4229f8ff7b01fd3f80969158c2aa147002cff7f93718bbf22b2ee9c
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• Hypothetical teaching process using existing T700/epoxy laminate properties and illustrative cure parameters, not a calibrated pultrusion recipe. Constant-speed moving section; no axial conduction, impregnation, leakage, die thermal mass or pulling-force prediction. Use Thermal Run, not batch-cycle 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: e4b5bd2f61d49b51556725754539ebab2d8918556588b75d611816c0009c3f19
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 8f45fd6c46d0a4405091972a67b224da3b52babc8dd3d87f19f001aab61029cd
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 5032172566d1841e5a1e0bd0a9b8c80ffb21c768bc3100fa8dce8171fd3c26ed
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 06e51e3ee91c7f1337f7afe8dc48e8069abcfeca070263914f746f012195f525
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 3d9c608cdc762900f7a6520398d636eddb36e93d75cf786d6b860b48f15959c6
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: fd8fb3dfd1a0a7138e7afea57a91d51c55100d00d7f239ebd7318a6e1fc8437c
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: a051d4d1f8929e41c52fac13bf4b86d044bbbd5051ab955d942845d96e489e88
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 23ccaabb1a97c4f66755f1c1969e25b4db913cff6ab08b82b3dc2af7b0ded4b5
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: bae683ad1c2436884bc7bb3b16c3385dd742d9621966d27129531a740a2a1181
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 7ea2c7180f0168bfbb7480a7e7654e8bf6c2ff3bdcf8df678c1de4e2ab73f55b
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 9b3a40b3e848a34f28da4f6bcff086af78b209f1b1adc3d3d82fab20ac501a1d
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 7523c43bf03a83535c8c87659219ede2c6c5710643c6c68fafd8838339ab80b8
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 95501614d40d50a0cc57ed5ef905f7b147e68a015d4fe4d2d52192900c6d24dd
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: afef050b92c692fd0c8de5573648c98852aefe5b27fb2250c61808c937b27404
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 4a5bddd06758ff4b6ac242771b46888abaa13a92ccb5860904552ae2d578800b
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 5686bf9157945a97d266389c321b4cf24bcbc14b61da2f8e22f664763ca5a617
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 2312902a264b8c82e768c422173d8881d1f114f35ec7697a044d023e0dc0c59d
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 730c2a27319a52380a698f21a567bb4a6682c4533f806aa001451c6c50209ca8
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: d274eebcd6feca036cd37a4ecc718c4466e0994bd7a4747a2ef1e025f9185230
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 741a24fac420fd716b27632f2bd9bc79873769a34552127eec10d6b6ad1507e4
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: faa486eb8709e65fd64336520d60269132d1a6a9d177e8210794e31c04eca1c5
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 69e0b3f866ccd2e2a1fb354a126acf791dc81f645d6a983e8e9fdb0a04343636
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 94dcc28d885b34ec9f17c5acb656ccd4d669a1c0d491438bd56ebec2f7e46cdf
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: cdd41f10d6b0605eb884e376bd661c10eaee16edd6c67e0518a8477a4c3da818
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: cac86dc8c5e41136fb851010fcc1e5887704cf4aa36ecf6691ea19482a58f840
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: c18dca6f058f05d82277b3656ceb2623c3a9fdd400b7ba63f9253045ec3c4454
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 09ccbe5586dedae6ac517ea03a9e392bd155d5e2494ab03ca9b364ae264c5840
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 3193e6c9b789d005f48ee1758367041ab8f1e8fe506344552b7cff8bb5906ddc
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 2de126d40e1c5392a8abaa33c39421fd13280b3a7ff4f9ffd8d5734deb3ad3e9
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 201882bb678ffd94b9c0072f7d96d0670cfe10df67aea650907feb8aa3aac373
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 920e29a7313d5b80da997fa3bd5ce19db90bc51be24fc324a377afbe02b1c634
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 76a43488e143e9f96e3f213be16693c5282b0a76e596c90802c7e37b1e03ddbd
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 52e5a2cd61276884851896b42f6c685aba1eb0c8ab6515728de80f1afea76983
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: c7bb9aa473dd603a0d10c0e5a22f72defa64908e888992eeeab0e51b1703a78b
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 4c68cd5157ddb323a6590a70999a2a6668c398cca511c98d65d7fe4cc94466e4
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 75924ab54654809ea11e5f0ffb0d978974327d25d665acfa9406e02b3f08c39b
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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)

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: 337f9c695d1966dbec169e97c238d4a7cf05af0ba6069df3079535c98c793417
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 5c90167875840cb61ff7d5f67136f43060e3824203ee5fdc70d36e5929359368
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 0f74d74518f7ccbadae572ee331bdf3ea00a125f8855ec33bbe08ac80e9829ab
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 7ea7e7cb4fadb49579e2d69d8bed46c19ad864ebe8a42ab9ddad7b394f3d996b
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: dc37525c569465ebb5dca006893adafbc1e49c00f43defd19376e6049a7001ed
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 10dd87e053aa96a6c886dbb82e72606a6a33720b8a6bcbdbb5849ce6e74a5ee0
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 2bb1078eec6b3f3c0c2cf7c33b0bbfe362178729d628d7ea35988bc1d33cfba9
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 4ca32ece47372d9a5c7b437fb4388924679f1b575f1e1b5aa6f0089ed712c15f
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: d25c36b2a749bbe4ee9cc3fa1dbb5e042c28b79987a933f28c452cd16651f502
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 74d3b99e8177b69424846dd7fb5a497fd2f9a26c38408f37e644bc7d97f662c5
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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)

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: f68147d0923f85babab732d1769070b138f4a0fb151062086aca5e199531c2a9
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 3d7a459998cd269ee6371bb1311defef33bbdea7ab9b6602c14adc69af501038
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 9afbefbc81228991ee6f22b0bf7f97c9509d0934ea0da2a23c9e90aa4ee465fa
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 18108142776a1a2dd71a69e63c2a3beac5d04995b2b75f8c3b425ef150ada4bb
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: c87dfc37ce0e5dd5dfecf0e15380a96d4cc1c828d19dc68b668646d7f57d8c22
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 4f030987cc2a7e4106cf2851cd1e820c130318fd48047e6607d13b67c3a2e6da
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 9bf71b536f18e33d2cfbdb89a98302664dd4bf5ceb79e65bb361d3aff20b66dc
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 531de6ae1c9c5e82ea1b2a11d809c90786b484feda8e63844469750de2cffd6a
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 95a65d7a7ccf744a9e9e5d0d99cc001ad58096606a1f2cd3554502d7e4e9772a
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 5918f2def49740ac43d473415a639706935b6b7b93e61c9108a53e1c9234864f
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 232aed539940bd02d774d7ba2c8a3dc9e589b13a249c55872bd99a533a1e5909
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 27c7c2b3d0af86fe976eee86ae2f373d1cd3d09a9b5d65fbeb7982cb1f94766f
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 20f72fdc58166b094497e0b66581b52868755b5397f826316a78b18b7df94e82
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 3098fed4ba840d8d72b2c55c477f396dc9a475c89f02404fc5c38ceb378ef51d
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 754e3e6c6d659e9e75d6efc67a282e80bb9c985dfdf93b50f4d12261d66d67c9
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: c66bcd8993b0272d6bf666a46ed60daff08b33ec861f7a70e875199c44499431
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: e51838e56c398120bafc34a20a4dea68862e699c20e8ca2330ba35c539d46231
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 8686ffa96b9424f4a79158c89c6847ab787efe6f899aae036ee993e8baab8920
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 8e62848b75f8e6b3e6d016c3c03ab63e84cd02c981768c08d816b75801344d74
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: 988393ea8f5c1fb7ee702650579eb91f568edf98fc0624ce09527e5c42326689
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: b126def56b8becee88d391f6a59b8d1640801214824b8fde9368125c6897162d
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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)

• 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":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":90,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":-45,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":0,"t":0.125},{"e1":139.38,"e2":6.4126394052044615,"g":2.987551867219917,"nu":0.26,"angle":45,"t":0.125}]

Input SHA-256: 4942472332999a655888f7d06f885011628940acf09202025bf122a71a476322
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: cd22fbf1390242ebf06aaa1c6bb92da7199d6032e09cb8854e9369b36749c2fc
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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: a58db2c57e7d4cea9f23784307eb42ba5209ccc26b8de1a7779a9cacfd6a64bd
Solver source SHA-256: 30c8a614b6cb004a26da8adaf8ab7c534c37c4d534836921939f35a549e1bcc5

• 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.