摘要
超声速射流逆流通常用于导弹、航天飞机、卫星和飞船等飞行器运动状态的控制。欠膨胀超声速射流逆流的流场包含有多激波（如弓形激波和马赫盘）、接触间断和剪切层，其结构非常复杂。本文采用激波高分辨率有限差分（ＴＶＤ）格式，对恒定自由流条件，各种不同射流出口压比的超声速轴对称道射流进行了数值模拟，且对各种条件下的物理现象给予了分析。计算的马赫盘和弓形激波位置与实验值相吻合，为此类流动问题提供了一种有效的预测方法。
Jet counterflow is usually used for the motion state control of aerospacecraft such as a missile, a shuttle, a satellite, and a spaceship, etc. The flowfields of an underexpanded jet counter to a supersonic stream containing multi shock (e.g. bow shock and Mach disk), contact discontinuities and shear layers are very complicated. In this paper,a high resolution scheme for shock wave is employed to solve axisymmetric jet counterflows, which are formed by the same counterflow Mach numbers with various jet exit pressure ratios. The physical phenomena corresponding to these results are analyzed. The calculating positions of Mach disk and bow shock wave are in agreement with experiment data.An effectiye prediction method for such problems is presented.
出处
《空气动力学学报》
CSCD
北大核心
1996年第2期200-204,共5页
Acta Aerodynamica Sinica
