Abstract:
This paper presents a comparison of pressure distributions obtained from theory and from wind-tunnel tests on two swept-back wings at various incidences and Mach numbers. The first wing, having NACA 65A004, sections had a taper ratio 0.2, an aspect ratio of 3, and had its quarter-chord line swept back through 45 deg. The second wing had RAE 102 sections, a taper ratio of 1/3, an aspect ratio of 2~/2, and had its semi-chord line swept back through 45 deg. The experimental flow conditions and patterns are presented in greater detail in Refs. 1 and 10, and are briefly discussed here insofar as they are relevant to the comparisons.
