Reynolds Number and LeadingEdge Bluntness Effects on a 65 o Delta Wing

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 a systematic variation of the leading edge bluntness. The analysis for this paper is focused on the Reynolds number and bluntness effects at transonic speeds (M = 0.85) from this data set. The results show significant effects of both these parameters on the onset and progression of leadingedge vortex separation. AR NOMENCLATURE wing aspect ratio, 1.8652 ble leading-edge bluntness, rle/cbar b/2 wing semispan, 1.0 ft. Cp pressure coefficient Cp,le leading-edge pressure coefficient Cp,v vacuum pressure coefficient Cp * sonic pressure coefficient c wing chord cbar wing mean aerodynamic chord, 1.4297 ft. cr wing root chord, 2.1445 ft. ct 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 cbar rle streamwise leading-edge radius S wing reference-area, 2.1445 ft 2 t wing thickness, 0.875 in. t/cbar nondimensional wing thickness, 0.051 wts NTF test section width, 8.2 ft. x,y,z Body-axis Cartesian coordinates xm,zm match coordinates, leading-edge contour α angle of attack η percent semispan location, 2y/b wing leading-edge swee