高超声速飞行器边界层外缘参数仿真分析  

Simulation analysis of outer edge boundary parameters for hypersonic-glide vehicle

作　　者：孟竹喧 胡凡[1,2] 彭科[1] 张为华 

机构地区：[1]国防科技大学航天科学与工程学院,湖南长沙410073 [2]高超声速冲压发动机技术重点实验室,湖南长沙410073

出　　处：《国防科技大学学报》2016年第2期31-36,共6页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(51406230)

摘　　要：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。Method of inviscid flow field simulation of the outer edge boundary layer for hypersonic vehicle was created, which was faster than the numerical method and more accurate than the engineering method. And the curve of specific heat and the specific heat ratio changed with temperature were matched, which deduced the law of air attribute on different temperatures. Based on the law, the model of parameters of the outer edge boundary layer for hypersonic vehicle was built, and the comparisons of the results of the proposed method and the engineering method as well as the viscid method of blunt double-cone model were analyzed. Result shows that at the 0° angle of attack, compared with the viscid method, the maximum differences of the pressures between engineering method and viscid method are about 1.19% and 2. 39% respectively, while at the 10° angle of attack, they are about 5% and 50% respectively. And the proposed inviscid numerical method obtained higher accuracy is superior to the engineering method, which lays the foundation for the thermal environment calculation of hypersonic-glide vehicle.

关 键 词：高超声速飞行器 比热/比热比 空气属性 无黏流场仿真 边界层外缘参数 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]