Thornel T-500 (Union Carbide) carbon fibre 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 -65 °F to 250 °F, consistent with moderately elevated service. MatWorld carries 8 tensile 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.
8 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 | |
|---|---|---|---|---|---|
Elongation at Break(εf) | 0.5800 – 1.390 | - | 8 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 7.000 – 329 | ksi | 12 entriesClick to expand | ||
Young's Modulus(E) | 1,100 – 25,100 | ksi | 12 entriesClick to expand | ||