Question: A symmetric supersonic airfoil has its upper and lower surfaces defined by a sine wave shape: where t is the maximum thickness, which occurs at

A symmetric supersonic airfoil has its upper and lower surfaces defined by a sine wave shape: where t is the maximum thickness, which occurs at x = C/2. Use Ackeret theory to derive an expression for the drag coefficient at zero angle of attack. Compare your result with Ackeret theory for a symmetric double-wedge airfoil of the same thickness.

A symmetric supersonic airfoil

v=-sin-

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