关键词: 超声速进气道;均匀超声速流;二维流;弯曲激波;附面层分离;数值仿真

Abstract: Compression surfaces are designed by using short lines with equal compression angle or increasing compression angle.Two dimensional supersonic flow fields are investigated when incoming flows pass through the compression surfaces.The results show that the compression surfaces can shape curved shock and pressure gradient along the surfaces is nearly constant,but the magnitude of constant pressure gradient depends on arrangement of short lines.It is shown that inlets with the non-conventional compression surfaces are more advantageous in keeping the stability of boundary layer than that one with conventional compression surfaces and their performance are similar at design point,but at off design point,the performance of inlets with non-conventional compression surfaces are better.

Key words: Supersonic inlets;Uniform supersonic flow;Two dimensional flow;Curved shock;Boundary layer separation;Numerical simulation