Exercise validation study
validation data, not blanket passes.

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 09ee8825ffe43c602514d52300580409a29fb5b758e828568779051e89923f19
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: abf46c5d9e8a9dfbbe4afc7981f48c68e710a20032b3d1c2fa2aed75f1406abe
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 3a2d51c115b2debb0883c5d150330d044589a986f3fd1eaeea75bf83356f7e7a
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: fbe62ccf3f67fddf86e0c552a77184206f996d9560e3d96fb21b212565536907
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: ba41accfb5e0b704588e4ff94716bd72bcc490a9a6d04681b9cf2360da4dc697
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: a36b418bece26734a28da085d823554ee5dcc8e914443cc2ecfd9216814a4f00
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 73500ec48dcf98642af3ec9439f5866e4959b4bc4343099a19b18961cb9d9124
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: cb6efa92f6b12cd7b88acab692bd47542d9010e4777d5feb4b174f16c7212729
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 576ab10ad3f2bd57a7cc26b9be69c202ee209b6f2226de19af0773d7d571b518
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 327323e824b9056b99474a72cafeb118c2a02f6acfa32e24bf821f6be3e7c0d9
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 347985308f2e8f31452d49d0eadd84dac06bf5a975c1b2a3235c339fd4e581e1
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: d0fd342461f9224fff5514e4153cb194297311c03e898190c0ad73ffd9537fc6
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

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

Input SHA-256: 0dbb6730c687f68001da36a1472a5e64ea06fadd782709f02017abe8944c3e03
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Micro closure requires a separate published benchmark

Tested inputs

Input SHA-256: 3ba3472a0772896a42073defe597b3c88730c368bd92fca0f9242628b42f0a32
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: f5824635696a3ac93f4e679c1408649ac5a84ce9f34b17ac61e38d91090b8bf6
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 5650561acf4398c19b9d71c18cfe45a813f2978d0ef1753d6dcfd99a6203fb80
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 37ebed2e201944e45d70adac2069b337d21fa2bbaaadd4cf937280c7b36fac5e
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 5aef363d4e967d0651232223ec2335e131e8804965b9066fc09c92833821e5dd
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 66d221e8490b5fc81796709d4ef093ca43bda6ae504c422db0230ea0697585db
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 254ee71029bf94d510bfcddb7316f37db23e0ce5f83b935c4b0735087d568d2a
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 53025665481f586aacbf98c49664f1cf5192d246ec424c40cef64547553ebcb1
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: e3b53be454de7eea87dd1b8ef948f3537735bafd5a638d68e585363c06502a84
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 9b7e5052fed096c06b2a9639e70fd17c8529a93b396c385a16ffa49fb987cc46
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 962dfac04a22eabc6b492e52d69d5b2867ae210a994e6881cac1c6cc10f42de2
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

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

Tested inputs

Input SHA-256: 98f09a9b013eb9fdb5252ce3245d15829776d94ac0390f4c85b46c581c424865
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 62f30905ca77e7a9ea034fc9ccd4f6a70c3df7f709fae5acfdd161ac19d43652
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 55b3335c1c86a130941cab76e2594f7310aa4cc0e5c7f4426c14485eaab65655
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 3740c9bf401dfb1fdb4fc00d69f397766f01821b9122b1dcf6fe715563d14060
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 5a9c1dc3b32dbc936af4fcffdb63b4bd76f1d7c04e5d8d461281bdbc0fcac31f
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 4f841617ab16c6d069e3711a6627acace0f2f62be01bd427ac49024d2f6c24d5
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 115ed18fb3cf180292ab9d21e7a1e63ed2a8d0e4c1fdde2228899a9b9d5b069f
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: ad152143b11dd823fd7333d33eb9a7696d43494965425ca194d7d92b277609c7
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: a9c9c3fed58a3635eb21c02b3f25a74989eb2753351b06998451195ec6a22901
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: a11419400ebfb7aaf0be87870dab78055ba732c0ddcc2179173a0016b0dd3590
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 45f2b86a6870d08091356a4b0c2a5eb62c6ccf05925504bf11abd5c8305c6e25
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 4aa848552959d19612295cdee85877df0397a4f25594ad16d81ea7bda9ff2b50
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 7ddb0362d0bed48c5db1f0e69eef4d36dcf2c68fcdf5a5f12b603422c1b7a81a
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: a4c21643271c4cb057844223a6826388c009229820915a2f491c7657a5169403
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 98c354018e6d7558648e9242f2a6eb5d9d60bb94d36e957e1be1b98f48860361
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: ab35018b0f2aafd0e3fb8a44c5189963b8db824a9d4f9abe066aac8e5afb5ad5
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 21fe94787fe294c7390258287989212a6ed98ded796ac2b69592d36dbdd3496b
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 0cec139ab12c72e3932b67398cf8149837cda9a262db10eab2992d26d02ee922
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 0359eb7afaf2ecb829de8178f3b17dd61d93095d3d8d0eda879c7164b60b9a98
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 7c36c80d45d35390d33cb2bc04d5f3fb66da0f7a12b89cf810279a2eeb0da551
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: e7f6ee65958e4f3d2be2eeb26bca39a18bfc5260acbc274eec0e2bad82c42123
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 2240afd942f6d9f374e6f271022b4697913a94820a64973cba7ec707082df984
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: c72091b31ddb24e202b88df19e0e2e39bda9538c646b3c0ce536c29e41834526
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 701cf1b0d772ee2f4d6eb5dd682129e5ab6405a6568cbf342b1a0e9d1d8e72a2
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 87dd820596d1893dcf8945b00297025084b5c0564fba075ee703cc4d051af676
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 2861990bc1508eafb0f9d4985215048990df032f99022e504b61eab9d724db7e
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: c1fdef2baf7308f13b1138a8104ddf56dc112fb32ad8731b7cea91a643a1d50a
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 87b83fdc6b249df93fe8a102d0d117985bf4f348eb8ed27f59fb0240517049a4
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 8ecac9aa05c325253c4973b69e22d5d97842003754f263dd23146fce0fac5ae3
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 365f43a2791e23d642c51680c9f6daaeaed94367bfe1d7d44153c5a49e98ab19
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 1a68eeaac3c9b60dca0d8675e1140946cd8a80897a6c398e1b4a8e1ac999b59a
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: d29d55ba73e3fccab2e990636e95779f9673872bb8fc0863a20e8b461b61ea28
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: fb60fe3f3623a6695a00a38744e49a56c503a06f0a6708c8b34c144b7b8e51c9
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: fda00a40ae393c9ea5a3dd65db141f4516045e7776cece6a8dad503c5443acf4
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 7c7aaad66d9dacc912f06749894fdfbcfa5b964d2f404b3993c77e6a5578a490
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 7f63910dbf30300cdc4d37ef43ccd93c41858fd055c5398231b2a5f47e0e1253
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 19656c8173fe255a53ba82f7e18639bde8b20a552e0718c4603e4b82e1d4a048
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: b01dce24a1f1d435674153a0fc543584371c592d8cf6f2126a96a727fe53d64b
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 4c5dd16ac39c58e97980371a1796d042ad6b573edcee34baab06cd7c197c14de
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 39ce6b729c327d2236e99ac7e29bca0424ea1a909091ca99d845da5655a0adbf
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 067d50f4f8a611aa96064b282a742c3a773c0512cfeaef2727983fd73d6f7f9a
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 56e4bc9be4ea7af24dfbe0d3b4b4a04e7b70daf3c620579e3c0cfd559be1fa44
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: a7fcdb66fb7e05b129298115a9a54338ace8a0b3ca3c59ad0bbffd45295c9e2f
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 66f80d23c56db1e5b110381a7c6cc8f2a3e49430ed44a6c158a7a4d1993170d9
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 1486f87aabf3fb929b18a85b56faee3ea44ee03353cee697f2c3097e44865468
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: babb1c725f0b6201ad87cafb409c5de29ed213e368d2d5a0f95d14b21139e831
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 6e58fbdf1856bde76658cde276572b95ee960ab4a199f37c22912572a12f7f11
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 9e686aaa98f23920edc02d039630ce3b70fd6b14c6450a14333823a7333eceb8
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: e4672b5c3e404967b7a6f1ae012de552fffaffaa35084325fd38d1c372f4d7ce
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 3ef73bcdba95d1ebd1ed193d9d9dad102d88023e7236be9f82eb4999b749a916
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: ab16c76917953b303d02a449a871f2b8cc7e1abaae9365ef85bad486b9e67516
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: e35c8e5feeb1d052fd136591e222f3ad9ccd4dafe6f9d4b83e1655896e36c7c0
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 6e07ab30a322e34cafd1f446efdc4c29e2a460b3c10d44bb8d889ef81a252e65
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: bcb8509e987b3bc0f5d8cfa0a503cface4ac183bf27f289ae07813a4e62f93f8
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: f62453c85c2edd4d286c1c612be58ebf066ba2ca312f19f5c92bba6fc3032068
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 16ff2c59431f45482fae332db196c92e9e0e7e22964e43a6ad8e6ff6c05b7606
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 65d5700ca68f222a1f1df47046a16387204fbcd2196f6e6bd8e38a557dea62e3
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: c860f6ba87ba3c133f8f1bedebdf46e9f71bc46d041dea9a12cfba4473d62473
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 5215ec27efb6cf7987a1d101571b93a37f312270ba1186db1afb02cd8a986b6e
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: a844a30953ad56ed97b41f55fa48d4f239bd1497c9dae49ecaba94b69ef6a263
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 17720e363539231df494589ad91cb1d9cff0b404692bd82d7eb17662c9445d4b
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 84d619dce4bb4ea8a9c4de1951edc3c4c9c6b1eba1a9336675897c461850f539
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 9bc77162b79035f3958d89105769d2fa4fb56a2b9696ce2dd772577c43e49d62
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 9a1ccb9529d054fdeb33cec76337f8d4edc13b6fe34383689632ec9cbd44905c
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 3f70529b583df639582b443aec929fd11ea7df2500a3bd986903e07313bcaf9a
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 2842e921172dda4de273997d3776f7fa9f5cdd9621f58a9ae30dc9b3873f2786
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 584de0edf69b6ee03b515bbb1f1fec67daef36300ddd7d96572b6fbf343c6ccd
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: ca93e26f7d103753684948c7ed5daf56faa263dfbeeb673eaf80869977946ce3
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 0e0b709a522d2944da588dc1934bcc14bcb2025923f1aa1ee90c13548a24aaa6
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 6d58b97daab8b0b7911e207be12a98e2f297dd8dac992dc0ffe59de54b1b255e
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 75e5e580f13c93544fda34a362425ebdfcca802e45f558c01bda8e0e44e48a2d
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: ff1bb666ddbfab7057a764ffd6811fb8716f47815b6a378790689962d427de04
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 7ebdc38c2959653ce75f0ce5e75a7f84e9a6e89b41e692f14ba63e6bcb514d1c
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: c0b1bb0ff562e0f3bd6eb750acaddf336f8f9ca778f6127436e1a76a0183f0ab
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 42ec0473c9398deea96ec7f0285739f1b106845b5a5094539163d26e8107d852
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 77aefd03dcde8ca00c673b7a6eee6b6fa5585b5f1debcd23dfd7d07397e4c087
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 96b6fb415367a905f0ca1916a499aa72de2c31fbfcb095af476da773f57e8aac
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 0eb1db8d7eaec66bfc5397a071339042ac518080aa9d0691b2332f270ea8852f
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: dee7877dc221d64263bcf31ffb373577e8bb756aa45f975df700edd32fc0c0f1
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 6fffc65ef74e198b4cb848772a2ee360db7aaaf7ad9c8294553570cfa1c28f11
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 695081389c7f28ffcf1afaea7fc891666a8d018f04e43c6fdb133232083aac0f
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 9c5d6613b92fda31dc00589066429fa5c3ecd35e35c62f1d813dc172ffa90e6b
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 4982b259465b360caf034ca9e60c032e1aaf47d28aaa3b79117d9653ef9afe90
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: a685a36c131f7a1d638e001922bccfbe6ffcd452039b6718c71e5a05445a4444
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 081adcf2ff7e3aff1655d4a095821dc254976198d22a119895f0fc102472240d
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: dac82ef38c8639bc250863471282d076335d7eea2098d5879f70aa36d27991c0
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: f42afe74836485494d81d1efc60d2106ba61d644efb9cd951ef0da9f0731e9e0
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 7e3a213bc948eb5152abf883739ee58c882f4b2568b5a9f585cc8e77dd218d03
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 6ed66fee58635d7525c4a61e10d1c70591beb3f858d00808f4a89843b2e2d47a
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 26e1d5b1b860ad30b356b70579cb1c596965a4300b4a56d1b26141fcbc2a5f59
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: a181d34ae5240afe0d31f2a206d55d1f3036c2cf12d4a7868a629d1eb3a5b711
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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: 6be9fe3290bb6804442d86f2119d1c13b8bacd68fe4a4278436478c1fecc94ad
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 3916c5a0466975139874a96c88b6de2379303ddebe22e4dbf70907448a1b371e
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 80309fc9fd2ac6a97f4997cc626e8f2aace26fabcc120d7e9ee5fd2520555312
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 3e5d7aea6b9956acd91f1c92cf77c52d10b7fb579fd8e59bf7d445472916a91f
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 064b9792b684169a05e202693bf2585d36e7fcb8c4b40dbaec6a674253ab1529
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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. Sequential outlet-state structural screening under a prescribed resultant; no pulling force, die friction, impregnation or load feedback into the thermal solution.

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: fd5f8410c1d843bb03c6025b9a6d5c9fb368a6bfea0ff4fe86b0a60f3f08babe
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 6c40936ce87e27ff80cc71e6670966804cb77afd8e99558bfa1890dd7a8b9016
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 840266629a7de8e545862e33f59022edcc8ecb034d1fdf0d023b575593f922c2
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: d174eb4409a649da49529166768d4c17478b83b64d7ec2357f654a56f4eb2a84
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: ff160b03af5c0af7bbcbf992a92132b9a484810df4e228a130ed4510ab477d8f
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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. Sequential outlet-state structural screening under a prescribed resultant; no pulling force, die friction, impregnation or load feedback into the thermal solution.

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 8af981c6feea22cec9248cbea320fbb0e20f97f433890259244015d5bbee0042
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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. Sequential outlet-state structural screening under a prescribed resultant; no pulling force, die friction, impregnation or load feedback into the thermal solution.

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 148b0d8f30d41fec4dcf5fcf0f315041be43fa7233c4c9a35f1ce2e3b2248a33
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 80220d253ce46314bf1cfdc6870ec9a8bd92de7e9b9962a448d8579380a3d002
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 363e42e708f6c434cbf12a2327a7237bfa823e8c11bc24ee2fa580779a887672
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 881dbbaf87187cfd51e01a58bf27fa3e62d06312a3a5025b29b4fa4786fdfafc
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: b600d98b0093e75fa292d1c3f4fa26a25ea3543e8ad8024567749abdedcd7da7
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 5c393c0b747d7c110b6604d2b63767ff2a386882d6ec87936bd638bd4f18c634
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: d545744383887aebad3be5bb05b0f3363cf97be6bd77cfbf7d7a676fe7719545
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: 728715b9c94e7ac0f13c860fa27e6a367c62dfc3892ded843bba20accbe83719
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

Input SHA-256: 7b496a06293dbbea8a5e6df5bfd6ed9529dd28a46048bd58ed28b82e5d734a35
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

Architecture needs a separate benchmark

Tested inputs

Input SHA-256: d6db8263464fe43ae49caadd528ae49093aae5dfff56a78fcbf819b2845473e2
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

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

Input SHA-256: c3288e99dacff32ef539d18da26bdf1186c963c7b436243f8bfccc58d880f8a5
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

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

Execution: Completed (not validation)

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

Tested inputs

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

Input SHA-256: 6c2710b7a3137f094e235172252ce779f3104a18d628ebeba117ca36e01c3f3f
Solver source SHA-256: 21b57ba5585334998ad98a0b2bac916764c93739a20e81f92e8e37cd50006f4a

• 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.