Investigation of the Effects of Sweep on the Characteristics of a High-Aspect Ratio Wing in the Langley 8-Foot High-Speed Tunnel

摘要

An untwisted wing, which when unswept has an NACA 65-210 section, an aspect ratio of 9.0 and a taper ratio of 2.5:1.0, has been tested with no sweep, and 30 deg and 45 deg of sweepback and sweepforward in conjunction with a typical fuselage at Mach numbers from 0.60 to 0.96 at angles of attack generally between -2 deg and 10 deg in the Langley 8-foot high-speed tunnel. Sweep was obtained by rotating the wing semispans about a point in the plane of symmetry. The normal-force, pitching-moment, profile-drag, and loading characteristics for the wings have been obtained from pressure measurements and wake surveys. The results indicate that the wings with /-30 deg of sweep experienced the severe changes in characteristics associated with the presence of a shock at higher Mach numbers then did the wing without sweep.