基于电子束电离的磁流体力学进气道流动控制数值模拟

采用基于电子束电离的磁流体力学(MHD)控制系统,对高超声速流场附面层,以及非设计状态下的高超声速进气道流场的磁流体控制进行了深入研究.控制方程为低磁雷诺数Navier-Stokes方程,采用等离子体动力学模型与电子束模型模拟空气电离过程.研究结果表明:①电子束电离能有效提高流场的电导率,增强磁场对流场的控制效率;②基于电子束诱导电离的MHD控制系统能有效地控制高超声速流场的附面层,但其控制效率跟电子束能量大小相关;③基于电子束诱导电离的MHD控制系统能有效地改变非设计状态下高超声速飞行器的斜激波结构,使进气道重新满足Shock-on-lip(SOL)条件,但进气道的总压恢复系数以及流量将会降低. 

Numerical simulation for magnetohydrodynamic inlets control using electron beam ionization

The magnetohydrodynamic (MHD) controlling of hypersonic boundary layer and hypersonic inlets in off-design conditions were studied by magnetohydrodynamic control system based on electron beam ionization.The governing equations were low magnetic Reynolds number Navier-Stokes(N-S) equations,and the plasma kinetics model coupled with electron beam model was developed to simulate air ionization.Results indicate :(1)The electron beam ionization can improve the conductivity of flow and the control efficiency of magnetic field .(2)The MHD system can effectively control the hypersonic boundary layer and the control efficiency closely related with the electron beam energy .(3)The MHD system can bring oblique shock in off-design conditions back to the location of shock-on-lip(SOL) condition,and the total pressure recovery coefficient and flow mass of inlets would be reduced.