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.
The working shear stress for the torsion member, whose cross section is shown in Figure P6.43, is 55 MPa.
a. Determine the design torque for the member.
b. Determine the shear stress in each segment of the cross section.
FIGURE P6.43
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