Flow over double-delta wing and wing body at high alpha

The effects of sideslip on the performance and stability of a double-delta wing and wing-body configuration were determined experimentally. The wake total pressure reveals the vortex size, location, and shape. Sideslip angle resulted in a decreased stall angle of attack, lower C/IV1AX, enhancement of post-stall lift recovery, increased upwind vortex sheet si/e, and decreased downwind vortex size. Adding the body to the wing increased the levels of adverse rolling and yawing moments at the stall. The wake surveys show that a narrow band at the edge of the vortex sheet has a very steep total pressure gradient present in all configurations. A b c() c c,, s 3