Numerical Simulation of Magneto-Hydrodynamics Effect on Supersonic Flow of A Projectile

Plasma actuator is an active flow control tool, which has been evaluated by the aerodynamic researchers since last decade due to its simple structure, light weight, low energy consumption, and high time response. In this paper effects of plasma on aerodynamic behavior of a rocket at different flight conditions is numerically investigated. Results of plasma effects or variation of attack angle, Mach number, and flight altitude on the drag and lift coefficients are evaluated. Applying plasma increases the vertical velocity under the rocket canards which leads to higher pressures and therefore higher pressure difference and forces are applied on the rocket canards which improves their functionality. Drag and lift coefficients are both increased due to the plasma, but the aerodynamic efficiency (lift to drag ratio) is increased by increasing potential difference. Results shows that plasma effect is reduced with increasing of angle of attack and increased with the flight altitude and aerodynamic efficiency is changed between %3 and %60 by applying plasma.