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Shown in Fig. P. 14.40 is the cross section of a thin-walled member which is part of an airplane wing. If the allowable shear stress is $5.5 \times 10^7 \mathbf{P a}$, find the allowable shear flow for this section and the stresses away from corners. Sides $A B$ and $C D$ have a thickness of 1 mm and sides $A C$ and $B D$ have a thickness of 2 mm . The mean height of the section is 265 mm and $G$ for the material is $2.8 \times 10^{10} \mathrm{~Pa}$. Assume no buckling. Find the allowable torque transmitted and the rate of twist. Figure P.14.40.

   Shown in Fig. P. 14.40 is the cross section of a thin-walled member which is part of an airplane wing. If the allowable shear stress is $5.5 \times 10^7 \mathbf{P a}$, find the allowable shear flow for this section and the stresses away from corners. Sides $A B$ and $C D$ have a thickness of 1 mm and sides $A C$ and $B D$ have a thickness of 2 mm . The mean height of the section is 265 mm and $G$ for the material is $2.8 \times 10^{10} \mathrm{~Pa}$. Assume no buckling. Find the allowable torque transmitted and the rate of twist.
Figure P.14.40.

Introduction to Solid Mechanics

Irving H. Shames,… 3rd Edition

Chapter 13, Problem 40

Instant Answer

Step 1

For sides $ AB $ and $ CD $ (thickness = 1 mm): \[ q_{AB} = \tau \cdot t_{AB} = (5.5 \times 10^7 \, \text{Pa}) \cdot (1 \times 10^{-3} \, \text{m}) = 5.5 \times 10^4 \, \text{N/m} \] For sides $ AC $ and $ BD $ (thickness = 2 mm): \[ q_{AC} = Show more…

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Shown in Fig. P. 14.40 is the cross section of a thin-walled member which is part of an airplane wing. If the allowable shear stress is $5.5 \times 10^7 \mathbf{P a}$, find the allowable shear flow for this section and the stresses away from corners. Sides $A B$ and $C D$ have a thickness of 1 mm and sides $A C$ and $B D$ have a thickness of 2 mm . The mean height of the section is 265 mm and $G$ for the material is $2.8 \times 10^{10} \mathrm{~Pa}$. Assume no buckling. Find the allowable torque transmitted and the rate of twist. Figure P.14.40.

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