AS4 12k (Hercules) carbon fibre (12,000-filament tow) in an E7K8 (U.S. Polymeric) 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.
Compliance & Regulations
Fiber Direction
Ply Schedule
Laminate Code
[0/0/0/0/0/0/0/0/0/0]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) | 15,700 – 20,400 | ksi | 8 entriesClick to expand | ||
Compressive Strength(σc) | 106 – 299 | ksi | 8 entriesClick to expand | ||
Elongation at Break(εf) | 1.080 – 1.600 | - | 6 entriesClick to expand | ||
Poisson's Ratio(ν)3 entries | 0.3200 n=5, 1 batches | - | 24°C · RTA · 12-axis · [0]:10 · as-measured | ||
| ↳ | 0.2880 n=5, 1 batches | - | 24°C · RTW · 12-axis · [0]:10 · as-measured | ||
| ↳ | 0.2880 n=5, 1 batches | - | 82°C · ETW · 12-axis · [0]:10 · as-measured | ||
Ultimate Shear Strength(Fsu)4 entries | 16.50 range 13.80–17.00n=20, 2 batches, CV 6.41% | ksi | 24°C · RTA · 12-axis · [(+-45):2/45]:s · as-measured | ||
| ↳ | 14.60 range 14.20–14.90n=5, 1 batches, CV 1.9% | ksi | 82°C · ETA · 12-axis · [(+-45):2/45]:s · as-measured | ||
| ↳ | 15.10 range 13.50–15.80n=5, 1 batches, CV 6.04% | ksi | 24°C · RTW · 12-axis · [(+-45):2/45]:s · as-measured | ||
| ↳ | 13.40 range 13.00–13.80n=5, 1 batches, CV 2.44% | ksi | 82°C · ETW · 12-axis · [(+-45):2/45]:s · as-measured | ||
Ultimate Tensile Strength(σUTS) | 4.100 – 347 | ksi | 9 entriesClick to expand | ||
Young's Modulus(E) | 1,160 – 21,800 | ksi | 9 entriesClick to expand | ||