Numerical simulation of wall temperature effect on compressive corner flow

Compression corner is a typical discontinuous region on hypersonic vehicle, and its separation/ reattachment structure has a great influence on the local thermal environment. In this paper, a self-developed program in-house DNS code is used to simulate the aerodynamic thermal dynamics of a typical compression corner in different wall temperatures. The results show that: with the increase of the wall temperature, the overall structure of the flow field changes little, but due to the large changes of the physical parameters of the fluid near the wall, the separation point of the corner separation vortex moves forward and the reattachment point moves backward, and the interference area at the corner expands; the heat flow in most regions of the compression corner decreases with the increase of the wall temperature, and the decrease range of the heat flow in the interference area is greater than that in the non interference area. However, the heat flux does not completely follow the law of decreasing with the increase of wall temperature. In addition, by comparing the calculation of heat flux with variable wall temperature and the correction of heat flux with hot wall correction formula, it is found that the accuracy of hot wall correction formula is reduced and the applicability is insufficient in the interference area. The research in this paper further deepens the understanding of the influence of wall temperature on the corner flow, and reduces the application scope of the hot wall correction formula.