The well-known methods of thin-airfoil theory have been extended to oblique or swept-back airfoils of finite aspect-ratio moving at supersonic speeds. The cases con¬sidered thus far are symmetrical airfoils at zero lift having-plan forms bounded by straight lines. Because of the conical form of the elementary flow fields the results are comparable in simplicity to the results of the two-dimensional thin-airfoil theory for subsonic speeds.
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