An orthotropic AS/3501 carbon/epoxy lamina (see Tables 2.2 and 4.1) is subjected to the plane stress condition \(\sigma_{x}=1000 \mathrm{MPa}, \sigma_{y}=50 \mathrm{MPa}\), and \(\tau_{x y}=50 \mathrm{MPa}\). If the lamina orientation is \(\theta=0^{\circ}\), will the lamina fail according to

(a) the maximum stress criterion or

(b) the maximum strain criterion?

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TABLE 2.2 Typical Values of Lamina Engineering Constants for Several Composites Having Fiber Volume Fraction U Material E [Msi (GPa)] T300/934 carbon/epoxy 19.0 (131) E2 [Msi (GPa)] 1.5 (10.3) G12 [Msi (GPa)] V12 Uf 1.0 (6.9) 0.22 0.65 AS/3501 carbon/epoxy 20.0 (138) 1.3 (9.0) 1.0 (6.9) 0.3 0.65 P-100/ERL 1962 pitch/ 68.0 (468.9) 0.9 (6.2) 0.81 (5.58) 0.31 0.62 carbon/epoxy IM7/8551-7 carbon/ 23.5 (162) 1.21 (8.34) 0.3 (2.07) 0.34 0.6 toughened epoxy AS4/APC2 carbon/PEEK 19.1 (131) 1.26 (8.7) 0.73 (5.0) 0.28 0.58 Boron/6061 boron/ 34.1 (235) 19.9 (137) 6.8 (47.0) 0.3 0.5 aluminum Kevlar 49/934 aramid/ 11.0 (75.8) 0.8 (5.5) 0.33 (2.3) 0.34 0.65 epoxy Scotchply 1002 E-glass/ 5.6 (38.6) 1.2 (8.27) 0.6 (4.14) 0.26 0.45 Boron/5505 boron/epoxy 29.6 (204.0) 2.68 (18.5) 0.81 (5.59) 0.23 0.5 Spectra 900/826 4.45 (30.7) 0.51 (3.52) 0.21 (1.45) 0.32 0.65 polyethylene/epoxy E-glass/470-36 E-glass/ 3.54 (24.4) 1.0 (6.87) 0.42 (2.89) 0.32 0.30 vinylester