An experimental investigation was performed in which surface pressure data, flow visualization data, and force and moment data were obtained on four conical delta wing models which differed in leading-edge camber only. Wing leading-edge camber was achieved through a deflection of the outboard 30 percent of the local wing semispan of a reference 75° swept flat delta wing. The four wing models have leading-edge deflection angles 6F of 0°, 5°, 10°, and 15° measured streamwise. Data for the wings with 6F = 10° and 15° showed that hinge-line separation dominated the lee-side wing loading and prohibited the development of leading-edge separation on the deflected portion of wing leading edge. How¬ever, data for the wing with 6F = 5° showed that at an angle of attack of 5°, a vortex was positioned on the deflected leading edge with reattachment at the hinge line. Flow visualization results have been presented which detail the influence of Mach number, angle of attack, and camber on the lee-side flow characteristics of conically cambered delta wings. Analysis of photographic data identified the existence of 12 distinctive lee-side flow types. In general, the aerodynamic force and moment data correlated well with the pres¬sure and flow visualization results.
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