T300 (Toray) carbon fibre (3,000-filament tow) in an EA 9396 (Dexter-Hysol) epoxy matrix. 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. Dry carbon fabric impregnated with epoxy resin in a wet lay-up impregnation process. MatWorld carries 26 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.
26 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) | 5,940 – 12,000 | ksi | 20 entriesClick to expand | ||
Compressive Strength(σc) | 19.80 – 96.80 | ksi | 20 entriesClick to expand | ||
Elongation at Break(εf) | 0.1930 – 1.430 | - | 20 entriesClick to expand | ||
Poisson's Ratio(ν) | 0.03700 – 0.05900 | - | 10 entriesClick to expand | ||
Shear Modulus(G) | 153 – 1,080 | ksi | 8 entriesClick to expand | ||
Ultimate Shear Strength(Fsu) | 3.820 – 21.80 | ksi | 8 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 56.70 – 110 | ksi | 20 entriesClick to expand | ||
Young's Modulus(E) | 7,010 – 10,400 | ksi | 20 entriesClick to expand | ||