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) | 53.09 – 70.33 | GPa | 8 entriesClick to expand | ||
Compressive Strength(σc) | 318.5 – 965.3 | MPa | 8 entriesClick to expand | ||
Interlaminar Shear Strength(ILSS)4 entries | 75.15 range 66.88–82.05n=15, 3 batches, CV 6.09% | MPa | 24°C · RTA · 13-axis · [0:f]:14 · as-measured | ||
| ↳ | 57.92 range 55.85–60.67n=9, 3 batches, CV 2.5% | MPa | 93°C · ETA · 13-axis · [0:f]:14 · as-measured | ||
| ↳ | 75.15 range 68.95–78.60n=15, 3 batches, CV 3.47% | MPa | 24°C · RTW · 13-axis · [0:f]:14 · as-measured | ||
| ↳ | 36.54 range 35.85–37.92n=12, 3 batches, CV 2.3% | MPa | 93°C · ETW · 13-axis · [0:f]:14 · as-measured | ||
Ultimate Tensile Strength(σUTS) | 676.4 – 917.0 | MPa | 8 entriesClick to expand | ||
Young's Modulus(E) | 46.19 – 76.53 | GPa | 8 entriesClick to expand | ||