AS4 (Hercules) carbon fibre (3,000-filament tow) in a 3501-6s (Hercules) epoxy matrix, supplied as 5-harness satin 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]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 Strength(σc)4 entries | 854.9 range 744.6–992.8 | MPa | 24°C · RTA · 1-axis · [0:f]:6 · norm. thk+Vf | ||
| ↳ | 882.5 range 765.3–1020n=30, 10 batches, CV 6.74% | MPa | 24°C · RTA · 1-axis · [0:f]:6 · as-measured | ||
| ↳ | 758.4 range 662.6–841.2n=30, 10 batches, CV 6.31% | MPa | 93°C · ETA · 1-axis · [0:f]:6 · norm. thk+Vf | ||
| ↳ | 779.1 range 682.6–861.8n=30, 10 batches, CV 6.24% | MPa | 93°C · ETA · 1-axis · [0:f]:6 · as-measured | ||
Interlaminar Shear Strength(ILSS)2 entries | 75.84 range 62.05–91.01n=30, 10 batches, CV 10.8% | MPa | 24°C · RTA · 13-axis · [0:f]:6 · as-measured | ||
| ↳ | 65.71 range 57.92–74.46n=30, 10 batches, CV 6.7% | MPa | 93°C · ETA · 13-axis · [0:f]:6 · as-measured | ||
Ultimate Tensile Strength(σUTS)2 entries | 772.2 range 672.9–848.1n=30, 10 batches, CV 5.78% | MPa | 24°C · RTA · 1-axis · [0:f]:8 · norm. thk+Vf | ||
| ↳ | 792.9 range 689.5–868.7n=30, 10 batches, CV 5.55% | MPa | 24°C · RTA · 1-axis · [0:f]:8 · as-measured | ||
Young's Modulus(E)2 entries | 67.09 range 61.57–69.64n=30, 10 batches, CV 2.48% | GPa | 24°C · RTA · 1-axis · [0:f]:8 · norm. thk+Vf | ||
| ↳ | 68.95 range 63.43–71.02n=30, 10 batches, CV 2.31% | GPa | 24°C · RTA · 1-axis · [0:f]:8 · as-measured |