AS4 3k (Hercules) carbon fibre (3,000-filament tow) in an E7K8 (U.S. Polymeric) epoxy matrix, supplied as plain weave. 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
[0/0/0/0/0/0/0/0/0/0/0/0]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)2 entries | 9,020 range 7,870–10,500n=210, 18 batches, CV 5.24% | ksi | 24°C · RTA · 1-axis · [0:f]:12 · norm. thk+Vf | ||
| ↳ | 8,070 range 7,070–9,040n=210, 18 batches, CV 4.28% | ksi | 24°C · RTA · 1-axis · [0:f]:12 · as-measured | ||
Compressive Strength(σc)2 entries | 111 range 64.40–138n=206, 18 batches, CV 11.7% | ksi | 24°C · RTA · 1-axis · [0:f]:12 · norm. thk+Vf | ||
| ↳ | 98.70 range 58.00–122n=206, 18 batches, CV 11.4% | ksi | 24°C · RTA · 1-axis · [0:f]:12 · as-measured | ||
Elongation at Break(εf) | 1.160 range 0.8820–1.500 | - | 24°C · RTA · 1-axis · [0:f]:12 · as-measured | ||
Interlaminar Shear Strength(ILSS) | 9.680 range 7.530–14.20n=170, 16 batches, CV 12% | ksi | 24°C · RTA · 13-axis · [0:f]:12 · as-measured |