Thornel T-300 (Union Carbide) carbon fibre (15,000-filament tow) in a 976 (Fiberite) epoxy matrix, supplied as tape. 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 -67 °F to 350 °F, consistent with elevated-temperature service. MatWorld carries 20 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]s
Fiber angles relative to the 0° reference direction (red arrow in 3D view). 0° = longitudinal, 90° = transverse, ±45° = shear paths.
20 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) | 1,250 – 29,600 | ksi | 15 entriesClick to expand | ||
Compressive Strength(σc) | 17.30 – 254 | ksi | 15 entriesClick to expand | ||
Elongation at Break(εf) | 0.1900 – 4.630 | - | 20 entriesClick to expand | ||
Interlaminar Shear Strength(ILSS) | 7.710 – 19.60 | ksi | 5 entriesClick to expand | ||
Poisson's Ratio(ν) | 0.3120 – 0.3480 | - | 5 entriesClick to expand | ||
Shear Modulus(G) | 770 – 1,000 | ksi | 5 entriesClick to expand | ||
Ultimate Shear Strength(Fsu) | 0.7000 – 13.70 | ksi | 5 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 2.670 – 256 | ksi | 15 entriesClick to expand | ||
Young's Modulus(E) | 1,160 – 24,900 | ksi | 14 entriesClick to expand | ||