Thornel T-300 (Toray) carbon fibre (3,000-filament tow) in a 934 (Fiberite) 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 250 °F, consistent with moderately elevated service. MatWorld carries 18 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
[0/0/0/0/0/0/0/0/0/0/0/0]s
Fiber angles relative to the 0° reference direction (red arrow in 3D view). 0° = longitudinal, 90° = transverse, ±45° = shear paths.
18 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) | 51.02 – 73.08 | GPa | 16 entriesClick to expand | ||
Compressive Strength(σc) | 262.0 – 958.4 | MPa | 24 entriesClick to expand | ||
Elongation at Break(εf) | 0.7750 – 1.240 | - | 8 entriesClick to expand | ||
Interlaminar Shear Strength(ILSS)3 entries | 82.74 range 72.39–92.39n=20, 4 batches, CV 6.89% | MPa | 24°C · RTA · 13-axis · [0:f]:12 · as-measured | ||
| ↳ | 82.05 range 68.95–95.84n=20, 4 batches, CV 8.38% | MPa | -54°C · CTA · 13-axis · [0:f]:12 · as-measured | ||
| ↳ | 63.43 range 62.74–65.50n=5, 1 batches, CV 2.1% | MPa | 121°C · ETA · 13-axis · [0:f]:12 · as-measured | ||
Ultimate Tensile Strength(σUTS) | 420.6 – 813.6 | MPa | 24 entriesClick to expand | ||
Young's Modulus(E) | 46.88 – 89.63 | GPa | 24 entriesClick to expand | ||