超音速气流绕局部透气凹角流动的数值模拟

以具有压力分裂形式的简化Ｎ Ｓ方程为控制方程，数值模拟了超音速来流条件下的激波 边界层干扰被动控制（ｐａｓｓｉｖｅｃｏｎｔｒｏｌｏｆｓｈｏｃｋ ｂｏｕｎｄａｒｙｌａｙｅｒｉｎｔｅｒａｃｔｉｏｎ）。模拟是以预先给定激波前吹气和激波后吸气的流量来实现的。为了定性地确定吹气或吸气对激波 边界层干扰的影响，首先计算了单独吹气和单独吸气两种情况。数值计算时采用了多重扫描法对控制方程差分离散，以反映亚音速区压力对流场的椭圆性影响。

COMPUTATION OF SUPERSONIC SEPARATED FLOW OVER THE COMPRES SION CORNER WITH LOCAL BLOWING AND SUCTION

Numerical solutions of supersonic separated flow over the compression corner with blowing and suction in the shock region are presented. The effects of blowing only or suction only on the shock boundary layer interaction are firstly studied. Then the emphasis is put on the flow with a combination of suction downstream and blowing upstream the shock, which is equivalent to the method of passive control of the shock boundary layer interaction. The results show that this control method has the potential to weaken the shock wave and reduce the shock induced separation tendency in the condition of supersonic flows. The numerical algorithm used in this paper is based on the pressure splitting form of the reduced Navier Stokes equations, and a multiple marching technique is applied to solve the discretised form of the RNS equations.