T650-35 (ICI Fiberite) carbon fibre (12,000-filament tow) in a 976 (ICI Fiberite) 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.
Compliance & Regulations
Fiber Direction
Ply Schedule
Laminate Code
[0/0/0/0/0/0/0/0/0]T
Fiber angles relative to the 0° reference direction (red arrow in 3D view). 0° = longitudinal, 90° = transverse, ±45° = shear paths.
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Compressive Modulus(Ec)3 entries | 1,380 range 1,230–1,440n=9, 3 batches, CV 5.48% | ksi | 22°C · RTA · 2-axis · [90]:22 · as-measured | ||
| ↳ | 1,550 range 1,450–1,660n=8, 3 batches, CV 4.11% | ksi | -55°C · CTA · 2-axis · [90]:22 · as-measured | ||
| ↳ | 1,080 range 940–1,210n=10, 3 batches, CV 8.38% | ksi | 121°C · ETW · 2-axis · [90]:22 · as-measured | ||
Compressive Strength(σc) | 15.30 – 44.60 | ksi | 5 entriesClick to expand | ||
Shear Modulus(G)3 entries | 745 range 680–830n=30, 5 batches, CV 4.82% | ksi | 22°C · RTA · 12-axis · [+/-45]:4s · as-measured | ||
| ↳ | 919 range 700–1,050n=30, 5 batches, CV 10.4% | ksi | -55°C · CTA · 12-axis · [+/-45]:4s · as-measured | ||
| ↳ | 542 range 510–580n=30, 5 batches, CV 3.91% | ksi | 121°C · ETW · 12-axis · [+/-45]:4s · as-measured | ||
Ultimate Shear Strength(Fsu) | 8.570 – 19.20 | ksi | 6 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 1.320 – 295 | ksi | 16 entriesClick to expand | ||
Young's Modulus(E) | 820 – 24,800 | ksi | 9 entriesClick to expand | ||