DECELERATION OF SUPERSONIC PLASMA FLOW BY AN APPLIED MAGNETIC FIELD

The problem of gas flow control by a magnetic field is considered as applied 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 magnetogas dynamic interaction, a numerical investigation was conducted. The results demonstrate the possibility of controlling the flow structure at reasonable plasma and magnetic field parameters. The effects of magneto-gas dynamic interaction on supersonic flow deceleration are investigated.