AS4 (Hercules) carbon fibre in a 3501-6 (Hercules) epoxy matrix, supplied as tape. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost. The handbook characterises it from -65 °F to 200 °F, consistent with moderately elevated service. MatWorld carries 4 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
Compliance & Regulations
Fiber Direction
Ply Schedule
Laminate Code
[0]T
Fiber angles relative to the 0° reference direction (red arrow in 3D view). 0° = longitudinal, 90° = transverse, ±45° = shear paths.
4 interactive curves for this material
Stress-strain, S-N fatigue and environmental knockdown curves are free with an account.
Create free account| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Compressive Modulus(Ec) | 83.43 – 187.5 | GPa | 12 entriesClick to expand | ||
Compressive Strength(σc) | 0.2890 – 1.889 | GPa | 15 entriesClick to expand | ||
Interlaminar Shear Strength(ILSS) | 57.23 – 133.8 | MPa | 6 entriesClick to expand | ||
Poisson's Ratio(ν) | 0.3000 | - | notes | ||
Shear Modulus(G) | 5.930 | GPa | notes | ||
Ultimate Tensile Strength(σUTS) | 0.04688 – 2.275 | GPa | 13 entriesClick to expand | ||
Young's Modulus(E) | 7.584 – 155.8 | GPa | 13 entriesClick to expand | ||
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Glass Transition Temperature(Tg) | 473 | K | notes | ||
Thermal Conductivity(k) | 0.6000 | W/(m·K) | T | ||
Coefficient of Thermal Expansion(α (CTE)) | 0.0000250 | 1/K | T |
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Density(ρ) | 1.580 | kg/m³ | — |