A cross section of the leading edge of an airplane wing is shown in Figure P6.111. The enclosed area is 82 \text { in. }^{2} . Sheet thicknesses are shown on the diagram. For an applied torque of T = 100 kip-in., determine the magnitude of the maximum shear stress developed in the section. (Note: The dimensions shown are measured to the wall centerline.)
Question 6.111: A cross section of the leading edge of an airplane wing is s...
The maximum shear stress for a thin-walled section is given by Eq. (6.25)
\tau_{\max }=\frac{T}{2 A_{m} t}The maximum shear stress developed in the section is:
\tau_{\max }=\frac{T}{2 A_{m} t}=\frac{100 kip – in .}{2\left(82 in .^{2}\right)(0.050 in .)}=12.20 ksi
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