Research on Hypersonic Aerodynamic Force Control by Arc Plasma Energy Deposition
Active flow control technology has the advantages of fast response,simple structure and flexible operation.It has a great potential application in spacecraft design.In this paper,the Ma 6 wind tunnel experiment has been carried out for hypersonic oblique shock control by using plasma energy deposition.A flat plate model combined with a ramp is used.The control effect of plasma energy deposition between two pairs of electrodes on hypersonic oblique shock is obtained with high-speed schlieren imaging technology.The flow field characteristics and parameters under the energy deposition are simulated by solving Reynolds averaged Navier-Stokes equations with an energy source term.The experimental results showed that due to the thermal effect of plasma energy deposition,compression waves are induced at the plate wall and a relatively sustainable plasma layer was formed,which weakened the hypersonic oblique shock;The numerical results showed that due to the weakening of the shock wave,the pressure on the ramp wall covered by the plasma layer is decreased,and the aerodynamic force of the model is changed significantly.When the instantaneous power of energy deposition is 4000W,the wave drag reduction rate is as high as 55.4%,the change rate of pitch torque is 6.9%,and the lift change is not obvious.It is found that under the control of plasma energy deposition,the reattachment point of oblique shock moves upward along the compression surface of the ramp,and the greater the instantaneous power of energy deposition,the thicker the plasma layer,and the greater the corresponding wave drag reduction rate.Finally,the control principle of hypersonic aerodynamic force/torque with plasma energy deposition is clarified.
NETL
NSTL
万方数据
维普
