高超声速流动与换热数值仿真研究

Numerical Study on Hypersonic Flow and Aerodynamic Heating

基于有限差分法开发了高超声速流动与换热问题气热耦合仿真求解器,运用该求解器对三种典型高超声速流动与换热问题开展了仿真研究,得到了相应的气动参数、热流密度分布.高超声速后台阶的存在使表面气动参数、热流分布不再连续;随着缝深的提高,缝隙局部流速迅速降低,对流换热效应减弱;高超声速无限长圆管绕流中,边界层外部区域气动参数随时间变化不大,边界层内存在较大的温度梯度,壁面温度随时间升高.三个算例的仿真结果均与试验测量值进行了对比,验证了所开发的求解器的计算能力.

A finite-difference unsteady coupled heat transfer solver was developed.This solver was utilized to simulate the hypersonic flow over a backward-facing step with a transverse gap,and the unsteady thermal conduction in an infinite circular pipe.The backward-facing step leads to local dramatically changing distributions of aerodynamic parameters and wall heat fluxes.The gas flow in the gap decelerates rapidly along with the increase of the gap depth,and there is rather weak convective heat transfer at the bottom of the gap.In the case of hypersonic flow around the infinitely long circular pipe,there exists large temperature gradient in the boundary layer,and the wall temperature increases with time,otherwise the aerodynamic parameters outside the boundary layer change quite slightly.The predicted results are in good agreement with the tested data.The comparison between numerical simulation results and tested data verifies the calculation ability of the developed solver.