Deceleration of supersonic plasma flow by an applied magnetic field

The problem of gas flow control by a magnetic field is considered as it applies to flows in the intakes of supersonic aircraft. The method to be discussed for control of the intake operation consists of a preliminary ionization of incoming gas and subsequent control of the ionized flow by an applied magnetic field. To estimate the prospects of such a mode for flow control and the effects of the magnetogasdynamic interaction, a numerical investigation was conducted. The results demonstrate the possibility of controlling the How structure at reasonable plasma and magnetic field parameters. The effects of magnetogasdynamic interaction on supersonic flow deceleration are investigated.