The aircraft members are made of aluminum (G = 27.0 GPa) and have a length of 1.0 m, unless otherwise stated. Assume that the stress concentrations at corners are negligible.
A torque T = 9.50 kN • m is applied to the torsion member whose cross section is shown in Figure P6.42. Determine the maximum shear stress in the member.
FIGURE P6.42
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