超声速边界层内小激波的数值模拟(英文)  

Numerical Simulation of Shock-Lets within the Supersonic Boundary Layer

作　　者：Shen Qing Zhang Hanxin Yuan Xiangjiang (China Aerodynamics Research and Development Center,Sichuan Mianyang 621000) 

出　　处：《空气动力学学报》2000年第z1期109-114,共6页Acta Aerodynamica Sinica

基　　金：National Laboratory for Computational Fluid Dynamics

摘　　要：本文通过有限差分计算求解了ＮＳ方程，对超声速二维平板边界层的非线性稳定性问题进行了模拟。流场的来流马赫数为４．５。平板从尖前缘开始，流场在前缘处产生一道前缘激波。数值计算模拟了边界层对成倍频关系的双频扰动波的吸收问题。通过计算发现，在一定频率下边界层内可出现小激波。计算给出了小激波的发展过程。In ths paper, the non-linear stability of a two-dimensional supersonic boundary layer over a fist plate is studied numerically by solving Navier-Stokes equations with a finite difference method. The now field with the incoming flow Mach number of 4.5 includes the leading edge of the flat plate where a leading edge shock wave generates. The numerical simulation was made on the receptivity of boundary layer to two disturbance waves which frequencies are of double multiple relation. The numerical result shows that shock-lots occur within the limited region of the boundary layer.

关 键 词：数值模拟 稳定性 边界层 

分 类 号：V211.42[航空宇航科学与技术—航空宇航推进理论与工程]