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
[0/0/0/0/0/0/0/0]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) | 6.688 – 142.0 | GPa | 8 entriesClick to expand | ||
Compressive Strength(σc) | 0.1055 – 1.737 | GPa | 18 entriesClick to expand | ||
Shear Modulus(G)4 entries | 3.744 range 3.420–4.089n=33, 5 batches, CV 5.16% | GPa | 24°C · RTA · 12-axis · [+-45]:4s · as-measured | ||
| ↳ | 5.302 range 5.088–5.950n=23, 5 batches, CV 3.69% | GPa | -54°C · CTA · 12-axis · [+-45]:4s · as-measured | ||
| ↳ | 1.496 range 1.165–1.793n=33, 5 batches, CV 9.25% | GPa | 82°C · ETW · 12-axis · [+-45]:4s · as-measured | ||
| ↳ | 972.2 range 710.2–1413n=41, 5 batches, CV 17.9% | MPa | 121°C · ETW · 12-axis · [+-45]:4s · as-measured | ||
Ultimate Shear Strength(Fsu) | 71.02 – 111.7 | MPa | 7 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 0.01138 – 2.186 | GPa | 20 entriesClick to expand | ||
Young's Modulus(E) | 6.274 – 164.8 | GPa | 8 entriesClick to expand | ||