Effects of aspect ratio on air flow at high subsonic Mach numbers

W. F. Lindsey, Milton D. Humphreys
Jul 1952

Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to 2 on the air flow past a wing at high subsonic Mach numbers. The results indicated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation.

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