Engineering, 25.03.2020 03:44 Jasten
Consider a circular cylinder (oriented with its axis perpendicular to the flow) and a symmetric diamond-wedge airfoil with a half-angle of 5° at zero angle of attack; both bodies are in the same Mach 5 freestream. The thickness of the airfoil and the diameter of the cylinder are the same. The drag coefficient (based on projected frontal area) of the cylinder is 4/7. Calculate the ratio of the cylinder drag to the diamond airfoil drag. (Round the final answer to one decimal place.)
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Consider a circular cylinder (oriented with its axis perpendicular to the flow) and a symmetric diam...
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