AN 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 BACA 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° and 45° 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° and 10° in the Langley 8-foot high-speed tunnel. Sweep was obtained by rotating the wing semi spans 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° of sweep experienced the severe changes in characteristics associated with the presence of shock at higher Mach numbers than did the wing without sweep.