锥柱裙类组合体类高超声速飞行器外部存在弓形激波,拐角诱发激波/边界层干扰,气动加热较为复杂。为深入研究此类气动热变化规律,采用CFD方法研究HIFiRE-4再入大气层气动热问题。结果显示,飞行器进入稀薄流区时,需重点关注鼻锥气动加热,而拐角气动加热不明显;进入稠密大气层后,飞行器拐角出现边界层分离与再附现象,且分离泡随着空气密度增大而逐步缩小,气动加热较为突出。

There is a shock wave in the outer edge of the spherical head of a hypersonic vehicle, and there is a shock wave-boundary layer interaction on the corner. Then, the aerodynamic heating is a littile complicated. In order to study aerodynamic heating of cone-cylinderflare configuration reentry vehicles, the CFD method was used to study the aerothermodynamics of HIFIRE-4. The results show that, we need to take consideration the aerodynamic heating on nose while in rarefied flow area, for the separation bubble cannot reattach to the flare, and the reattachment heating is not obvious in the corner. But in continuous flow area, there is a change, the separated shock wave reattached to the flare completely, the separation bubble with the gradual narrowing tends to be stable, the aerodynamic heating problems become very prominent.