AS4 (Hercules) carbon fibre (3,000-filament tow) in a 3501-6 (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. The handbook characterises it from -65 °F to 200 °F, consistent with moderately elevated service. MatWorld carries 4 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
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.
4 interactive curves for this material
Stress-strain, S-N fatigue and environmental knockdown curves are free with an account.
Create free account| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Compressive Modulus(Ec) | 6,420 – 10,200 | ksi | 10 entriesClick to expand | ||
Compressive Strength(σc) | 49.80 – 145 | ksi | 10 entriesClick to expand | ||
Interlaminar Shear Strength(ILSS)4 entries | 9.930 range 8.500–10.70n=9, 3 batches, CV 7.38% | ksi | 24°C · RTA · 13-axis · [0]:15 · as-measured | ||
| ↳ | 7.940 range 7.600–8.400n=9, 3 batches, CV 3.89% | ksi | 93°C · ETA · 13-axis · [0]:15 · as-measured | ||
| ↳ | 9.350 range 9.000–9.600n=6, 2 batches, CV 2.22% | ksi | 24°C · RTW · 13-axis · [0]:15 · as-measured | ||
| ↳ | 11.30 range 10.10–12.10n=15, 3 batches, CV 5.05% | ksi | 24°C · RTA · 13-axis · [0:f]:s · as-measured | ||
Ultimate Tensile Strength(σUTS) | 93.30 – 146 | ksi | 10 entriesClick to expand | ||
Young's Modulus(E) | 8,250 – 13,100 | ksi | 10 entriesClick to expand | ||