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 | 124 range 108–144 | ksi | 24°C · RTA · 1-axis · [0:f]:6 · norm. thk+Vf | ||
| ↳ | 128 range 111–148n=30, 10 batches, CV 6.74% | ksi | 24°C · RTA · 1-axis · [0:f]:6 · as-measured | ||
| ↳ | 110 range 96.10–122n=30, 10 batches, CV 6.31% | ksi | 93°C · ETA · 1-axis · [0:f]:6 · norm. thk+Vf | ||
| ↳ | 113 range 99.00–125n=30, 10 batches, CV 6.24% | ksi | 93°C · ETA · 1-axis · [0:f]:6 · as-measured | ||
Interlaminar Shear Strength(ILSS)2 entries | 11.00 range 9.000–13.20n=30, 10 batches, CV 10.8% | ksi | 24°C · RTA · 13-axis · [0:f]:6 · as-measured | ||
| ↳ | 9.530 range 8.400–10.80n=30, 10 batches, CV 6.7% | ksi | 93°C · ETA · 13-axis · [0:f]:6 · as-measured | ||
Ultimate Tensile Strength(σUTS)2 entries | 112 range 97.60–123n=30, 10 batches, CV 5.78% | ksi | 24°C · RTA · 1-axis · [0:f]:8 · norm. thk+Vf | ||
| ↳ | 115 range 100–126n=30, 10 batches, CV 5.55% | ksi | 24°C · RTA · 1-axis · [0:f]:8 · as-measured | ||
Young's Modulus(E)2 entries | 9,730 range 8,930–10,100n=30, 10 batches, CV 2.48% | ksi | 24°C · RTA · 1-axis · [0:f]:8 · norm. thk+Vf | ||
| ↳ | 10,000 range 9,200–10,300n=30, 10 batches, CV 2.31% | ksi | 24°C · RTA · 1-axis · [0:f]:8 · as-measured |