06.4 / Worked examples

Explore a study.
Continue it as an exercise.

Examples and exercises share one curriculum: the same inputs, model choices, tasks and limitations. Choose a checked baseline, then explore a more recent coupled study.

DifficultyEstimated walkthrough

About difficulty levels and time estimates

Instructional ratings describe setup and interpretation effort, not solver accuracy or license access. Existing catalog stages remain separate. Estimates include setup, comparisons and interpretation; they are not solver runtimes and will vary with experience.

Foundation — a single basic material or micromechanics relationship.
Developing — orientation, short-fiber comparisons or an introductory laminate setup.
Intermediate — a structural response, transport history or process study.
Advanced — coupled fields, nonlinear response or optimization with more interpretation.
Integrated — a multi-field study combining thermal, moisture and mechanical effects.

The numbered ring fills as difficulty increases. The clock fill indicates walkthrough duration on a two-hour scale; the adjacent number gives the estimate in minutes. These initial ratings are assigned from the model scope and curriculum stage and can be refined by instructors.

32 matching examples and stored-data studies

Baselines with recorded passing checks

The 2026-09-20 report checks specific quantities against analytical references. Passing those checks is not experimental validation, and does not certify an edited study or the current solver. Open the evidence below each example to see the tested scope, inputs and tolerances.

Workbench workflow

01.01 · Rule of mixtures: fibre volume fraction →

Level 1
FoundationEst. 15 min

View fixed-layout exercise workflow

01.01 · Rule of mixtures: fibre volume fraction · Fixed layout with all supplied blocks · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

01.01 · Rule of mixtures: fibre volume fraction · Used records in the universal fixed layout · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

Open the copied Micro record and identify its fibre and matrix materials.

Rule of mixtures · Voigt · Reuss

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

Open exercise →Open this exercise in Workbench ↗

Recorded checks · 2026-09-20

Reference validation · 2026-09-20

Benchmark validated — analytical scope

Listed reference-elastic extensional constants only; free curvature, ply stresses, strength and every user variation are outside this badge.

Recorded baseline only—not a certification of the current database, edited inputs, or every output. Analytical agreement is not experimental material or failure validation.

Source validation, comparisons and tested inputs

Execution: Completed (not validation)

Acceptance: absolute error ≤ absolute tolerance + relative tolerance × |reference|.
Quantity	CDS	Reference	Error %	Tolerance (relative + absolute)	Result
Ex (GPa)	51.01956	51.01956	0.000001713727	0.01% + 0.00002 GPa	Pass
Ey (GPa)	51.01956	51.01956	0.000001713727	0.01% + 0.00002 GPa	Pass
Gxy (GPa)	19.35659	19.35659	-0.000002845679	0.01% + 0.00002 GPa	Pass
νxy (—)	0.31789	0.317886	0.001260455	0.01% + 0.00002 —	Pass
Micro E1 (GPa)	139.38	139.38	0	0.01% + 0.00002 GPa	Pass
Micro E2 (GPa)	6.41264	6.412639	0.000009275362	0.01% + 0.00002 GPa	Pass
Micro G12 (GPa)	2.98755	2.987552	-0.0000625	0.01% + 0.00002 GPa	Pass
Micro ν12 (—)	0.26	0.26	0	0.01% + 0.00002 —	Pass

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

Reference ply list (GPa, mm, degrees)

[{"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.

Download source-validation results (JSON) · Full 138-exercise study

Laminates

02.08 · Laminate orientation and tensile response →

Level 2
DevelopingEst. 25 min

View fixed-layout exercise workflow

02.08 · Laminate orientation and tensile response · Fixed layout with all supplied blocks · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

02.08 · Laminate orientation and tensile response · Used records in the universal fixed layout · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

Open the copied laminate and record the initial stacking sequence and total thickness.

Classical laminate theory · Linear static · ASTM D3039-17(2025)-based

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

Open exercise →Open this exercise in Workbench ↗

Recorded checks · 2026-09-20

Reference validation · 2026-09-20

Benchmark validated — analytical scope

Listed reference-elastic extensional constants only; free curvature, ply stresses, strength and every user variation are outside this badge.

Recorded baseline only—not a certification of the current database, edited inputs, or every output. Analytical agreement is not experimental material or failure validation.

Source validation, comparisons and tested inputs

Execution: Completed (not validation)

Acceptance: absolute error ≤ absolute tolerance + relative tolerance × |reference|.
Quantity	CDS	Reference	Error %	Tolerance (relative + absolute)	Result
Ex (GPa)	51.92147	51.92147	-0.000007455559	0.01% + 0.00002 GPa	Pass
Ey (GPa)	51.92147	51.92147	-0.000007455559	0.01% + 0.00002 GPa	Pass
Gxy (GPa)	19.81407	19.81407	0.00001959758	0.01% + 0.00002 GPa	Pass
νxy (—)	0.31022	0.3102175	0.0007934734	0.01% + 0.00002 —	Pass

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

Reference ply list (GPa, mm, degrees)

[{"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.

Download source-validation results (JSON) · Full 138-exercise study

Workbench workflow

02.10 · Three-point bending: span and stiffness →

Level 3
IntermediateEst. 25 min

View fixed-layout exercise workflow

02.10 · Three-point bending: span and stiffness · Fixed layout with all supplied blocks · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

02.10 · Three-point bending: span and stiffness · Used records in the universal fixed layout · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

Inspect specimen width, laminate thickness, support span and central force.

Euler–Bernoulli beam · ASTM D7264-26-based

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

Open exercise →Open this exercise in Workbench ↗

Recorded checks · 2026-09-20

Reference validation · 2026-09-20

Benchmark validated — analytical scope

Central-load beam deflection and shear, conditional on the reported effective Ex. Material elasticity, ply stress and failure not validated.

Recorded baseline only—not a certification of the current database, edited inputs, or every output. Analytical agreement is not experimental material or failure validation.

Source validation, comparisons and tested inputs

Execution: Completed (not validation)

Acceptance: absolute error ≤ absolute tolerance + relative tolerance × |reference|.
Quantity	CDS	Reference	Error %	Tolerance (relative + absolute)	Result
Ex (GPa)	51.92147	51.92147	-0.000007455559	0.01% + 0.00002 GPa	Pass
Ey (GPa)	51.92147	51.92147	-0.000007455559	0.01% + 0.00002 GPa	Pass
Gxy (GPa)	19.81407	19.81407	0.00001959758	0.01% + 0.00002 GPa	Pass
νxy (—)	0.31022	0.3102175	0.0007934734	0.01% + 0.00002 —	Pass
Maximum deflection (mm)	1.213667	1.213667	0.00000745556	0.05% + 0.00002 mm	Pass
Maximum shear (N)	50	50	0	0.01% + 0.00002 N	Pass

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

Reference ply list (GPa, mm, degrees)

[{"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}]

Beam benchmark inputs

{"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.

Download source-validation results (JSON) · Full 138-exercise study

Workbench workflow

02.11 · Thin-wall pressure vessel →

Level 3
IntermediateEst. 30 min

View fixed-layout exercise workflow

02.11 · Thin-wall pressure vessel · Fixed layout with all supplied blocks · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

02.11 · Thin-wall pressure vessel · Used records in the universal fixed layout · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

Inspect the tube dimensions in Geometry and pressure/end conditions in CASES.

Thin-wall membrane · Classical laminate theory

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

Open exercise →Open this exercise in Workbench ↗

Recorded checks · 2026-09-20

Reference validation · 2026-09-20

Benchmark validated — analytical scope

Thin-wall pressure equilibrium and orthotropic biaxial strain comparison; stiffness inputs are conditional where Micro closure has not been verified.

Recorded baseline only—not a certification of the current database, edited inputs, or every output. Analytical agreement is not experimental material or failure validation.

Source validation, comparisons and tested inputs

Execution: Completed (not validation)

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

Acceptance: absolute error ≤ absolute tolerance + relative tolerance × |reference|.
Quantity	CDS	Reference	Error %	Tolerance (relative + absolute)	Result
Hoop stress (MPa)	56.4	56.4	0	0.01% + 0.00002 MPa	Pass
Axial stress (MPa)	28.2	28.2	0	0.01% + 0.00002 MPa	Pass
Hoop strain including Poisson coupling (µε)	755.3712	755.3698	0.0001824025	0.05% + 0.01 µε	Pass
Axial strain including Poisson coupling (µε)	246.3161	246.3132	0.001149021	0.05% + 0.01 µε	Pass

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

Pressure reference 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.

Download source-validation results (JSON) · Full 138-exercise study

Laminates

02.23 · T700/Epoxy Quasi-Isotropic · stored-data layup →

Level 2
DevelopingEst. 20 min

View fixed-layout exercise workflow

02.23 · T700/Epoxy Quasi-Isotropic · stored-data layup · Fixed layout with all supplied blocks · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

02.23 · T700/Epoxy Quasi-Isotropic · stored-data layup · Used records in the universal fixed layout · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

Trace the stored material-to-laminate path. Inspect original file, record ID, property status and units; Micro is intentionally not used.

Stored lamina elasticity · Classical laminate theory · Maximum stress

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.

Open exercise →Open this exercise in Workbench ↗

Recorded checks · 2026-09-20

Reference validation · 2026-09-20

Benchmark validated — analytical scope

Listed reference-elastic extensional constants only; free curvature, ply stresses, strength and every user variation are outside this badge.

Recorded baseline only—not a certification of the current database, edited inputs, or every output. Analytical agreement is not experimental material or failure validation.

Source validation, comparisons and tested inputs

Execution: Completed (not validation)

Acceptance: absolute error ≤ absolute tolerance + relative tolerance × |reference|.
Quantity	CDS	Reference	Error %	Tolerance (relative + absolute)	Result
Ex (GPa)	51.52598	51.52598	0.000006494251	0.01% + 0.00002 GPa	Pass
Ey (GPa)	51.52598	51.52598	0.000006494251	0.01% + 0.00002 GPa	Pass
Gxy (GPa)	19.67704	19.67704	0.00001957239	0.01% + 0.00002 GPa	Pass
νxy (—)	0.30929	0.3092921	-0.0006846539	0.01% + 0.00002 —	Pass

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

Reference ply list (GPa, mm, degrees)

[{"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.

Download source-validation results (JSON) · Full 138-exercise study

Structural response

02.37 · Quasi-Isotropic Plate in Uniaxial Tension · resultant response →

Level 3
IntermediateEst. 20 min

View fixed-layout exercise workflow

02.37 · Quasi-Isotropic Plate in Uniaxial Tension · resultant response · Fixed layout with all supplied blocks · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

02.37 · Quasi-Isotropic Plate in Uniaxial Tension · resultant response · Used records in the universal fixed layout · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

Trace the stored material-to-laminate path. Inspect original file, record ID, property status and units; Micro is intentionally not used.

Stored lamina elasticity · Classical laminate theory · Maximum stress

Open exercise →Open this exercise in Workbench ↗

Recorded checks · 2026-09-20

Reference validation · 2026-09-20

Benchmark validated — analytical scope

Listed reference-elastic extensional constants only; free curvature, ply stresses, strength and every user variation are outside this badge.

Recorded baseline only—not a certification of the current database, edited inputs, or every output. Analytical agreement is not experimental material or failure validation.

Source validation, comparisons and tested inputs

Execution: Completed (not validation)

Acceptance: absolute error ≤ absolute tolerance + relative tolerance × |reference|.
Quantity	CDS	Reference	Error %	Tolerance (relative + absolute)	Result
Ex (GPa)	51.52598	51.52598	0.000006494251	0.01% + 0.00002 GPa	Pass
Ey (GPa)	51.52598	51.52598	0.000006494251	0.01% + 0.00002 GPa	Pass
Gxy (GPa)	19.67704	19.67704	0.00001957239	0.01% + 0.00002 GPa	Pass
νxy (—)	0.30929	0.3092921	-0.0006846539	0.01% + 0.00002 —	Pass

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

Reference ply list (GPa, mm, degrees)

[{"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.

Download source-validation results (JSON) · Full 138-exercise study

Recent coupled-study exercises

Explore reaction heating, moisture-induced curvature and pultrusion. These exercises are selected from the maintained catalog; their teaching objectives are not claims of validated manufacturing predictions. The small diagrams show model connections, not calculated results.

Processing

03.58 · Pultrusion: thick-section cure lag and loaded stiffness →

Level 4
AdvancedEst. 40 min

View fixed-layout exercise workflow

03.58 · Pultrusion: thick-section cure lag and loaded stiffness — Material travels through the supplied heating and cooling die zones. Pulling speed sets residence time; inspect outlet temperature and cure where available. — **Physical process schematic** · Open full-size schematic ↗

03.58 · Pultrusion: thick-section cure lag and loaded stiffness · Fixed layout with all supplied blocks · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

03.58 · Pultrusion: thick-section cure lag and loaded stiffness · Used records in the universal fixed layout · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

Run the 4 mm profile at 0.1 m/min in the multi-zone die.

1D pultrusion thermal cure · Kamal–Sourour cure kinetics · CHILE cure-dependent modulus · Classical laminate theory · Thermomechanical coupling

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.

Open exercise →Open this exercise in Workbench ↗

Illustrative study · not presented as a verified benchmark.

Moisture

03.61 · Moisture plus applied bending: competing curvature contributions →

Level 4
AdvancedEst. 40 min

View fixed-layout exercise workflow

03.61 · Moisture plus applied bending: competing curvature contributions — Moisture enters or leaves the laminate through its prescribed surface conditions. Compare surface concentration, uptake and through-thickness diffusion. — **Physical process schematic** · Open full-size schematic ↗

03.61 · Moisture plus applied bending: competing curvature contributions · Fixed layout with all supplied blocks · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

03.61 · Moisture plus applied bending: competing curvature contributions · Used records in the universal fixed layout · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

Run the unsymmetric conditioned laminate with Nx = 25,000 N/m and Mx = 5 N per unit width.

1D transient moisture diffusion · Classical laminate theory · Hygromechanical coupling · Extension–bending coupling

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.

Open exercise →Open this exercise in Workbench ↗

Illustrative study · not presented as a verified benchmark.

Processing

03.62 · Thick laminate: reaction heating, cure gradient and process stress →

Level 4
AdvancedEst. 40 min

View fixed-layout exercise workflow

03.62 · Thick laminate: reaction heating, cure gradient and process stress — Surface boundary histories drive heat into and out of the laminate. Compare surface and core histories; include reaction heating only when enabled in the exercise. — **Physical process schematic** · Open full-size schematic ↗

03.62 · Thick laminate: reaction heating, cure gradient and process stress · Fixed layout with all supplied blocks · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

03.62 · Thick laminate: reaction heating, cure gradient and process stress · Used records in the universal fixed layout · not solved results — Exercise workflow · Open full-size map ↗Hide unused blocks
All blocks keep the CREATE / DISCOVER / SIMULATE positions, with Equipment below Geometry; unused records remain disconnected. This changes the view only, not the exercise records.

Run the 6 mm laminate through the 120°C dwell with its linked resin reaction heat.

Heat transfer · Classical laminate theory · Extension–bending coupling · Thermomechanical coupling

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.

Open exercise →Open this exercise in Workbench ↗

Illustrative study · not presented as a verified benchmark.

Original examples, within the curriculum

25 original stored-data studies already have exercise records, with source filenames, defined tasks and explicit limitations. Continue with these records instead of maintaining a second copy of the inputs.

Browse the converted studies

01.09 · T700S / 180C Epoxy UD · stored-ply elasticity 20 minOriginal stored data with a new explicit unit-resultant teaching load
01.10 · IM7 / Toughened Epoxy UD · stored-ply elasticity 20 minOriginal stored data with a new explicit unit-resultant teaching load
01.11 · T800S / BMI UD · stored-ply elasticity 20 minOriginal stored data with a new explicit unit-resultant teaching load
01.12 · AS4 / PEEK UD · stored-ply elasticity 20 minOriginal stored data with a new explicit unit-resultant teaching load
01.13 · T300 / EPON 862 Epoxy UD Prepreg · stored-ply elasticity 20 minOriginal stored data with a new explicit unit-resultant teaching load
01.14 · T800S / 977-3-Type Epoxy UD Prepreg · stored-ply elasticity 20 minOriginal stored data with a new explicit unit-resultant teaching load
01.15 · AS4 / LY 1564-Type Epoxy UD Prepreg · stored-ply elasticity 20 minOriginal stored data with a new explicit unit-resultant teaching load
01.16 · T300 / Phenolic Plain Weave · stored-ply elasticity 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.23 · T700/Epoxy Quasi-Isotropic · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.24 · IM7/Toughened Epoxy Bending-Optimized · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.25 · T800/BMI Balanced Cylinder · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.26 · AS4/PEEK Quasi-Isotropic · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.27 · T800/BMI Hoop-Dominant Cylinder · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.28 · T700/Epoxy Cross-Ply · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.29 · T700/Epoxy Balanced Angle-Ply · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.30 · IM7/Toughened Epoxy Unidirectional · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.31 · AS4/PEEK Cross-Ply · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.32 · T300/Phenolic Woven Symmetric · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.33 · T300/EPON 862 Quasi-Isotropic · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.34 · T800/977-3 Quasi-Isotropic · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.35 · AS4/LY 1564 Quasi-Isotropic · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.36 · IM7/8552-Type Quasi-Isotropic · stored-data layup 20 minOriginal stored data with a new explicit unit-resultant teaching load
02.37 · Quasi-Isotropic Plate in Uniaxial Tension · resultant response 20 minOriginal resultants, reference elastic CLT only
02.38 · Cross-Ply Plate under Pure Bending · resultant response 20 minOriginal resultants, reference elastic CLT only
02.39 · Angle-Ply Plate under Biaxial Load and Shear · resultant response 20 minOriginal resultants, reference elastic CLT only

Historical reference examples

The older web examples remain available for their sources and calculation context. They are historical demonstrations, not a statement of current Workbench verification.

Micromechanics archive Laminate archive Structural archive Legacy starter files

Explore a study.Continue it as an exercise.

Baselines with recorded passing checks

Reference validation · 2026-09-20

Tested inputs

Reference validation · 2026-09-20

Tested inputs

Reference validation · 2026-09-20

Tested inputs

Reference validation · 2026-09-20

Tested inputs

Reference validation · 2026-09-20

Tested inputs

Reference validation · 2026-09-20

Tested inputs

Recent coupled-study exercises

Original examples, within the curriculum

Historical reference examples

Explore a study.
Continue it as an exercise.