Reynolds Number and Leading-Edge Bluntness Effects on a 65 deg Delta Wing

ABSTRACT A 65 o delta wing has been tested in the National Transonic Facility (NTF) at mean aerodynamic chord Reynolds numbers from 6 million to 120 million at subsonic and transonic speeds. The configuration incorporated systematic variation of the leading edge bluntness. The analysis for this paper is focused on the Reynolds number and bluntness effects at subsonic speeds (M = 0.4) from this data set. The results show significant effects of both these parameters on the onset and progression of leading-edge vortex separation. NOMENCLATURE AR wing aspect ratio, 1.8652 b le leading-edge bluntness, r le /c bar b/2 wing semispan, 1.0 ft. C m pitching moment coefficient about 0.25c bar C N normal force coefficient C p pressure coefficient c wing chord c bar wing mean aerodynamic chord, 1.4297 ft. c r wing root chord, 2.1445 ft. c t wing tip chord, 0 ft. d sting diameter, 0.275 ft. d/b nondimensional sting diameter, 0.1375 M Mach number Rn Reynolds number, based on c bar r le streamwise leading-edge radius S wing reference-area, 2.1445 ft