Consider the thin walled cross-section of an aircraft wing shown below. It consists of two cells...

 

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Consider the thin walled cross-section of an aircraft wing shown below. It consists of two cells separated by a vertical web. Note the different skin thicknesses. 35 50 91 0.20 0.15 0.10 911 110 all dimensions in cm The shear flows in cell I (left); qi and cell II (right); qII due to an applied torque are given by: 91 = 48 N/cm 911 = 13 N/cm Determine the values of shear stress around the section and so find the value of the maximum stress in the section. Submit your answer in N/cm² to 1 decimal place, but without units. Consider the thin walled cross-section of an aircraft wing shown below. It consists of two cells separated by a vertical web. Note the different skin thicknesses. 35 50 91 0.20 0.15 0.10 911 110 all dimensions in cm The shear flows in cell I (left); qi and cell II (right); qII due to an applied torque are given by: 91 = 48 N/cm 911 = 13 N/cm Determine the values of shear stress around the section and so find the value of the maximum stress in the section. Submit your answer in N/cm² to 1 decimal place, but without units.

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Shear flow in cell I q 48 Nom Shear flow ... View the full answer