AS4 (Hercules) carbon fibre (12,000-filament tow) in a 3502 (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. Surface-treated.
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.
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Compressive Modulus(Ec) | 17,100 – 26,300 | ksi | 6 entriesClick to expand | ||
Compressive Strength(σc) | 139 – 307 | ksi | 6 entriesClick to expand | ||
Elongation at Break(εf) | 0.07770 – 2.120 | - | 9 entriesClick to expand | ||
Poisson's Ratio(ν)3 entries | 0.3400 n=30, 5 batches | - | 24°C · RTA · 12-axis · [0]:6 · as-measured | ||
| ↳ | 0.3560 n=20, 4 batches | - | 129°C · ETA · 12-axis · [0]:6 · as-measured | ||
| ↳ | 0.2800 n=25, 5 batches | - | 129°C · ETW · 12-axis · [0]:6 · as-measured | ||
Ultimate Tensile Strength(σUTS) | 2.540 – 358 | ksi | 9 entriesClick to expand | ||
Young's Modulus(E) | 950 – 22,200 | ksi | 9 entriesClick to expand | ||