Inviscid flow about airfoils at high supersonic speeds

A. J. Eggers, Jr., Clarence A. Syvertson
Mar 1952

Steady flow about curved airfoils is investigated analytically at high supersonic speeds. Assuming air behaves as an ideal diatomic gas, it is found that small pressure disturbances emanating from the surface of an airfoil are almost completely absorbed in the leading-edge shock wave (or a shock wave emanating from any other location on the surface), provided the flow deflection angles are not too close to those corresponding to shock detachment.

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