To explore the complex flow mechanism in the scramjet isolator under different wall heat transfer

the effects of wall temperatures on the oscillation characteristics of pseudo-shock in the scramjet isolator were investigated with a two-order accuracy unsteady computational fluid dynamics code. The numerical results show that there is a close relationship between the wall pressure histories and the maximum upstream and downstream locations of the shock-train leading-edge. Moreover

it shows that the fluctuating pressure amplitudes increase and frequencies decrease with the wall temperature. The maximum value of wall pressure standard deviation occurs at the place where the shock-train leading-edge shocks/boundary layer interact. However

the maximum values of kinetic energy are mainly in the shear layer region of the separation bubble.