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Cmh17 Fiber Reference: 6.2.3.4.2(a)

011 to 014

CMH-17/MIL-HDBK-17-3F fiber and reinforcement reference tables. Includes typical fiber properties (carbon, glass, aramid, boron), nominal composite properties for various reinforcement types, fiber sizing/finish compatibility data, and general reference data from MIL-HDBK-17-3F Chapter 2 and CMH-17 Chapter 6.

Aerospace Engineeringtable id: 6.2.3.4.2(a)4 rowsPage 2 of 2
table idrow indexc1c2c3c4contextsource page
6.2.3.4.2(a)011TITANIUM shear stress – ksi MPa peel stress – ksi MPa0.061 0.419 -0.067 -0.4650.338 2.33 -0.541 -3.732.27 15.64 -2.817 -19.43MIL-HDBK-17-3F Volume 3, Chapter 6 Structural Behavior of Joints TABLE 6.2.3.4.2(a) Generic mechanical properties of composites (Reference 6.2.3.4.2(a)). Unidirectional Lamina 0/90 Laminate Composite E L , E T , ν LT α L344
6.2.3.4.2(a)012STEEL shear stress – ksi MPa peel stress – ksi MPa peel stress – ksi MPa0.789 5.44 -0.914 -6.30 -3.54 -24.41.16 7.99 -2.17 -15.0 -5.82 -40.13.80 26.22 -5.52 -38.1 -6.47 -44.6MIL-HDBK-17-3F Volume 3, Chapter 6 Structural Behavior of Joints TABLE 6.2.3.4.2(a) Generic mechanical properties of composites (Reference 6.2.3.4.2(a)). Unidirectional Lamina 0/90 Laminate Composite E L , E T , ν LT α L344
6.2.3.4.2(a)013ALUMINUM shear stress – ksi MPa4.02 27.74.08 28.25.86 40.47MIL-HDBK-17-3F Volume 3, Chapter 6 Structural Behavior of Joints TABLE 6.2.3.4.2(a) Generic mechanical properties of composites (Reference 6.2.3.4.2(a)). Unidirectional Lamina 0/90 Laminate Composite E L , E T , ν LT α L344
6.2.3.4.2(a)014t -- 0.2 inch (5.08 mm); t adjusted for equal adherend stiffnesses; t = .01 inch (0.253 mm) i o b Adhesive properties: shear modulus -- 150 ksi (1.03 GPa) peel modulus -- 500 ksi (3.49 GPa) Cure temperature 250°F (121°C); Application temperature 75°F (24°C)MIL-HDBK-17-3F Volume 3, Chapter 6 Structural Behavior of Joints TABLE 6.2.3.4.2(a) Generic mechanical properties of composites (Reference 6.2.3.4.2(a)). Unidirectional Lamina 0/90 Laminate Composite E L , E T , ν LT α L344

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