Mechanism investigation on boundary layer affecting shock wave induced by plasma aerodynamic actuation

Based on the experimental result of inducing shock wave in a small-scale short-duration supersonic wind tunnel, this paper illustrated the theory of inducing shock wave that was not only lied on Joule heating effect but also decided by the discharge area thickness of boundary layer. Moreover, the experimental investigation on inducing plasma shock wave in the hypersonic wind tunnel in order to confirm such theory drew the conclusion that under the condition that the boundary layer is very thin the plasma aerodynamic actuation could induce oblique shock wave. This paper discussed the theory of inducing shock wave in these two different conditions and also confirmed the key effect of boundary layer in plasma and shock wave interaction. (authors)