Aerodynamic Effects of Thickness on 75° Delta Wings

Three 75° delta wings, at 8%, 10% and 13.5% relative thickness, were studied both experimentally and through simulations. The experiments were done at Mach numbers up to 0.195 and angles of attack from -6° to 34°. The experimental evaluation showed that air foil thickness substantially affects the aerodynamic response of 75° delta wings to changes in Mach number and angle of attack. The thicker wing demonstrated enhanced lift at higher speeds but was more susceptible to drag increase and potential early vortex breakdown. Meanwhile, the thinner wing offered more stable performance across the tested conditions. These insights are critical for optimizing delta wing designs in subsonic and transonic flight environments.