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.
Effects of Aspect Ratio on Air Flow at High Subsonic Mach Numbers
1952
12 pages
Report
Keine Angabe
Englisch