Study on Heat Flux Identification and Measurement Method for the Stagnation Point of Sharp Leading Edge Model in Arc-Heated Wind Tunnel

摘要

Near-space hypersonic vehicles use a sharp leading edge and a large lift-to-drag ratio profile, and the aerodynamic heating environment is extremely harsh. At present, in order to improve its performance and reduce costs, hypersonic vehicles are in urgent need of low-redundancy thermal-protection structure design, and require ground arc heating assessment tests to have better accuracy and repeatability. Because the stagnation radius of the leading edge is too small, the traditional heat flux measurement technology cannot measure the heat Mux density at the leading edge stagnation point. How to determine the tip front stagnation point heat flow in the arc wind tunnel condition is a technical problem to be solved urgently. In this paper, based on the experimental measurement and numerical analysis techniques, a method for identification and measurement of heat flux at the sharp leading edge stagnation point is proposed and verified by experiments. The results show that the method can obtain the heat flux distribution in the stagnation area of the leading edge with small leading edge radius, which has high credibility.