球头高超音速热绕流的研究

HYPERSONIC THERMAL ROUNDABOUT FLOW AROUND A SPHERICAL NOSE

本文研究了加热（冷却）对流动的影响。通过计算分析了在不同来流马赫数和加热量下，加热对球头高超音速绕流的影响规律。研究表明，加热对流动有着显著的影响，将使流动出现“热斥冷吸”、表面压力和激波距离增大、加热与冷却影响的非线性、加热使超音速区内马赫数下降趋向于１等现象。

The effect of heating on hypersonic flow around a spherical nose at Mach Number 8,12,15 and 20 is numerically studied in this paper.The physical mechanism that both the shock distance and the surface pressure increase when heating the gas is also given here.It is found that the effect of heating ill subsonic region of nose flow is very different from that of cooling.And the Mach Number will decrease to one if continuously heating in supersonic region of shock wave layer.