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) | 108.2 – 140.7 | GPa | 8 entriesClick to expand | ||
Compressive Strength(σc) | 0.7308 – 2.062 | GPa | 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 | 113.8 range 95.15–117.2n=20, 2 batches, CV 6.41% | MPa | 24°C · RTA · 12-axis · [(+-45):2/45]:s · as-measured | ||
| ↳ | 100.7 range 97.91–102.7n=5, 1 batches, CV 1.9% | MPa | 82°C · ETA · 12-axis · [(+-45):2/45]:s · as-measured | ||
| ↳ | 104.1 range 93.08–108.9n=5, 1 batches, CV 6.04% | MPa | 24°C · RTW · 12-axis · [(+-45):2/45]:s · as-measured | ||
| ↳ | 92.39 range 89.63–95.15n=5, 1 batches, CV 2.44% | MPa | 82°C · ETW · 12-axis · [(+-45):2/45]:s · as-measured | ||
Ultimate Tensile Strength(σUTS) | 0.02827 – 2.392 | GPa | 9 entriesClick to expand | ||
Young's Modulus(E) | 7.998 – 150.3 | GPa | 9 entriesClick to expand | ||