This 65-degree delta wing model test is part of an experimental and computational effort aimed at isolating the effects of Reynolds number, Mach number, and leading-edge radius on partial leading-edge vortex separation. Surface pressure measurments were taken in the Low-Turbulence Pressure Tunnel (LTPT) for a Reynolds number range from 1.5 to 12 Million over an angle of attack range from -2 to 30 degrees at Mach numbers of 0.2 and 0.4. This model is a 3/4-scale version of another 65-degree delta wing tested to full-scale Reynolds numbers in the National Transonic Facility.
