论文部分内容阅读
一、引言 在研究高超音速钝头体粘性气体绕流时,驻点区域的气动力参数和热力学参数的预报也是十分重要的。当粘性层很薄时,一直采用古典边界层方程计算;但是,考虑粘性气体与无粘流的相互干扰时,边界层模型已不适用,可用粘性激波层方程来描述极其广泛的来流马赫数及雷诺数的流场。 近年来,不少人致力于驻点线附近流场的计算,有的跨激波,有的分离激波。但
I. INTRODUCTION It is also very important to predict the aerodynamic parameters and thermodynamic parameters in the stagnation zone when studying the flow around the blunt body hypersonic viscous gas. When the viscous layer is very thin, classical boundary layer equations have been used; however, the boundary layer model is not applicable when considering the mutual interference of viscous gas and no-viscous flow. The viscous shock-wave equation can be used to describe the extremely broad flow Mach Number and Reynolds number flow field. In recent years, many people are committed to the calculation of flow field near the point line, and some trans-shock, and some separation of shock. but