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利用N-S数值解方法对高超声速气流中微型凸起物的气动热环境进行了计算研究,并对前斜坡峰值压力和热流跃升进行了分析,结果表明对于高雷诺数流动,由于其边界层很薄,气流对凸起物的冲击作用比低雷诺数流动大很多,给凸起物前缘和上表面带来较严重的气动热问题。研究还表明利用斜面侧扩张角可以降低凸起物后斜坡的气动热环境。最后对球锥与平板物型的差异给微型凸起物热环境特性带来的影响进行了研究,结果表明在本文计算状态下,风洞平板实验模型得到的凸起物前缘峰值压力和热流跃升比实际球锥外形要高,因此地面实验结果外推到天上实际情况还是比较保守的。
The aerodynamic thermal environment of microprotrusions in hypersonic airflow is studied by NS numerical solution method. The peak pressures and heat flux jerk of the front slope are analyzed. The results show that for the high Reynolds number flow, due to the thin boundary layer , The impact of the airflow on the bump is much larger than that of the low Reynolds number, which brings more serious aerodynamic heat problems to the leading edge and the upper surface of the bump. The study also shows that the use of bevel side flare angle can reduce the aerodynamic thermal environment of the back slope of the bump. Finally, the effect of the difference between the spherical cone and the plate shape on the thermal environment characteristics of the micro-bump was studied. The results show that the peak pressure and the heat flux of the bump front obtained by the wind tunnel experiment model in this paper, Jumped higher than the actual cone shape, so the experimental results of the ground extrapolation to the actual situation in the sky is still relatively conservative.