AS4 6k (Hercules) carbon fibre in a PR 500 RTM (3M) epoxy matrix. 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 -75 °F to 350 °F, consistent with elevated-temperature service. MatWorld carries 21 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
[0/0/0/0/0/0]s
Fiber angles relative to the 0° reference direction (red arrow in 3D view). 0° = longitudinal, 90° = transverse, ±45° = shear paths.
21 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) | 55.09 – 67.98 | GPa | 8 entriesClick to expand | ||
Compressive Strength(σc) | 291.0 – 972.2 | MPa | 20 entriesClick to expand | ||
Elongation at Break(εf) | 0.9700 – 1.640 | - | 10 entriesClick to expand | ||
Interlaminar Shear Strength(ILSS) | 35.85 – 87.56 | MPa | 6 entriesClick to expand | ||
Shear Modulus(G) | 1.310 – 6.157 | GPa | 15 entriesClick to expand | ||
Ultimate Shear Strength(Fsu) | 48.47 – 125.5 | MPa | 15 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 652.2 – 917.0 | MPa | 20 entriesClick to expand | ||
Young's Modulus(E) | 58.33 – 72.39 | GPa | 20 entriesClick to expand | ||