一种辅助高超音速进气道起动方法研究

用数值方法研究了楔角形内压缩进气道的起动过程,确定了研究楔角形进气道辅助起动方法是否有效的一般过程。研究了一种辅助进气道起动的方法,即将进气道突然暴露在高速气流之中。结果表明,降低进气道内初始压强,然后进行这种脉冲起动,可大大降低进气道的起动马赫数;发动机流道内初始压强对这种进气道辅助起动方法有重要影响,初始压强高于一定值时,该方法不产生作用。

Investigation on one aid hypersonic inlet starting method

The starting process of internal compression wedge inlet was investigated by means of numerical methods.The general process was presented to determine whether the aid inlet starting method is effective.An aid inlet starting method that the inlet was abruptly exposed in high-speed flow was investigated.The results show that inlet starting Mach number can be greatly decreased by means of reducing initial inlet pressure and pulse staring.The initial pressure has great effects on aid inlet starting method.When initial pressure is more than the certain value,this method is insensitive to initial pressure.