AS4 (Hercules) carbon fibre (3,000-filament tow) in a 3501-6 (Hercules) 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. 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) | 7,700 – 10,200 | ksi | 8 entriesClick to expand | ||
Compressive Strength(σc) | 46.20 – 140 | ksi | 8 entriesClick to expand | ||
Interlaminar Shear Strength(ILSS)4 entries | 10.90 range 9.700–11.90n=15, 3 batches, CV 6.09% | ksi | 24°C · RTA · 13-axis · [0:f]:14 · as-measured | ||
| ↳ | 8.400 range 8.100–8.800n=9, 3 batches, CV 2.5% | ksi | 93°C · ETA · 13-axis · [0:f]:14 · as-measured | ||
| ↳ | 10.90 range 10.00–11.40n=15, 3 batches, CV 3.47% | ksi | 24°C · RTW · 13-axis · [0:f]:14 · as-measured | ||
| ↳ | 5.300 range 5.200–5.500n=12, 3 batches, CV 2.3% | ksi | 93°C · ETW · 13-axis · [0:f]:14 · as-measured | ||
Ultimate Tensile Strength(σUTS) | 98.10 – 133 | ksi | 8 entriesClick to expand | ||
Young's Modulus(E) | 6,700 – 11,100 | ksi | 8 entriesClick to expand | ||