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 | 62.19 range 54.26–72.39n=210, 18 batches, CV 5.24% | GPa | 24°C · RTA · 1-axis · [0:f]:12 · norm. thk+Vf | ||
| ↳ | 55.64 range 48.75–62.33n=210, 18 batches, CV 4.28% | GPa | 24°C · RTA · 1-axis · [0:f]:12 · as-measured | ||
Compressive Strength(σc)2 entries | 765.3 range 444.0–951.5n=206, 18 batches, CV 11.7% | MPa | 24°C · RTA · 1-axis · [0:f]:12 · norm. thk+Vf | ||
| ↳ | 680.5 range 399.9–841.2n=206, 18 batches, CV 11.4% | MPa | 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) | 66.74 range 51.92–97.91n=170, 16 batches, CV 12% | MPa | 24°C · RTA · 13-axis · [0:f]:12 · as-measured |