An experimental study on the use of plasma to improve blunt body aerodynamics in a supersonic flow is presented. Shadow, schlieren, and plasma glow imaging techniques were used simultaneously for flow and plasma visualization. The discharge current and voltage, as well as the flow pressure and temperature at different locations on the surface of the model, were measured. With a proper aspect ratio 0.81 of the physical spike length to the frontal diameter of a 60-deg truncated cone-cylinder designed for the wind-tunnel model, the on-board pulsed electrical discharge produced a conically distributed plasma around the cathode, which modified the main shock wave structure from a detached bow shock to a tip attached conical shock wave
Read full abstract