临近空间高超声速稀薄流中梯形缝隙绕流分析

Aiming at the configuration characteristics of irregular gaps on the surface of hypersonic vehicle, it is simplified into a trapezoidal gap model. The direct simulation Monte Carlo (DSMC) method is used to simulate the flow around gaps in the hypersonic rarefied flow. The influence of different gaps wall angles on the flow field structure and wall parameters is studied, which provides numerical support for spacecraft structural design and thermal protection design. The results show that changing the wall angle will change the structure of the flow field. When the wall angle decreases, the external flow will penetrate deeper into the gap, which enhances the aerodynamic parameters of the flow field and surface in the gap, and the smaller the angle, the deeper the influence. When the angle is less than 30°, the vortex region in the gap completely disappears.