高超声速飞行器边界层外缘参数仿真分析

以高超声速飞行器为研究对象,构建快速准确计算高超声速飞行器无黏边界层外缘参数的计算方法。拟合空气比热、比热比随温度变化曲线,建立空气属性温度划分准则。基于不同空气属性建立高超声速飞行器边界层外缘参数工程与数值计算模型,采用钝双锥模型,对比分析工程估算、无黏数值及有黏数值计算方法的计算结果。结果表明,0°攻角状态下,基于无黏流场的数值计算与工程估算和有黏数值计算的压强最大差值分别为1.19%和2.39%;10°攻角状态下,最大差值分别为5%和50%;从而证明所提出的无黏数值计算方法明显优于工程计算方法,为进一步快速准确计算高超声速飞行器气动热环境奠定了重要基础。

Simulation and Analysis of Outer Edge Boundary Parameters for Hypersonic-glide Vehicle

Method of inviscid flow field simulation of the outer edge boundary layer for hypersonic vehicle was created, which is more faster than the numerical method and more accurately than the engineering method. And the curve of specific heat together with the specific heat ratio changed with temperature was matched, deduced the law of air attribute on different temperature. Based on the law, model of parameters of the outer edge boundary layer for hypersonic vehicle was built, and compered the result of method in this paper and the engineering method as well as the viscid method of blunt double-cone model. It shows that at the 0 degree angle of attack, the pressure of inviscid method in this thesis and engineering method compering to the viscid method have differences of 2.39% and 50%, while at the 10 degree angle of attack are 1.19% and 5%, which proved the inviscid numerical method in this thesis obtained higher accuracy, and laid the foundation of the thermal environment calculation.