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

W. F. Lindsey, Milton D. Humphreys
naca-tn-2720
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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