高超声速钝球柱外形表面热流分布研究  

Heat Flux Distribution Research of Hypersonic Blunt Sphere-cylinder Model

作　　者：张亮[1] 程晓丽[1] 艾邦成[1] 欧东斌[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《航天返回与遥感》2014年第1期13-20,共8页Spacecraft Recovery & Remote Sensing

摘　　要：文章采用数值求解雷诺平均Navier-Stokes方程方法对高超声速钝球柱地面试验模型进行了计算,比较了不同头部半径和肩部半径条件下表面热流的分布特征。研究表明:钝球柱头部区域表面热流分布与头部半径和肩部半径紧密相关。其中,头部半径对热流分布特征和热流大小均存在显著影响。当头部半径较小时,头部区域热流呈现双峰值分布,热流由驻点峰值逐渐下降,接近肩部时开始上升,至肩部峰值点后又继续下降。随着头部半径的增大,驻点热流减小,肩部热流增加,双峰值分布逐渐演变为单峰值分布,热流由驻点单调上升至肩部峰值点;相对于头部半径,肩部半径主要影响热流大小,驻点热流和肩部热流均随肩部半径的增大而增加,不同肩部半径计算模型的头部热流分布规律基本一致。Numerical simulation of blunt sphere-cylinder model is carried out by solving Reynolds aver-aged Navier-Stokes equations in this paper. The heat flux distributions with different nose radiuses and corner radiuses are compared. The results show that the characteristics of surface heat flux distribution within nose region are sensitive to nose radius and corner radius：nose radius has influence on both distribution and value of heat flux. When nose radius is small, there are two peak values within nose region：one is stagnation point and the other is around the corner. When nose radius increases, the stagnation heat flux decreases and the corner heat flux increases. At certain point, the heat flux distribution becomes monotone. Corner radius has only in-fluence on the value of heat flux. Both of the stagnation and corner heat flux increase with corner radius.

关 键 词：钝球柱形 气动特性 高超声速 热流分布 数值模拟 返回式航天器 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]