描述:
The potential of controlling shockwave–boundary layer interactions(SWBLIs) in air by plasma aerodynamic actuation is demonstrated. Experiments are conducted in a Mach 3 in-draft air tunnel. The separation-inducing shock is generated with a diamond-shaped
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The plasma synthetic jet is a novel active flow control method because of advantages such as fast response,high frequency and non-moving parts,and it has received more attention recently,especially regarding its application to high-speed flow control.In t
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For hypersonic flow,it was found that the most efective plasma actuator is derived from an electromagnetic perturbation.An experimental study was performed between hypersonic flow and plasma aerodynamic actuation interaction in a hypersonic shock tunnel,i
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An experimental investigation on airfoil(NACA64-215)shock control is performed by plasma aerodynamic actuation in a supersonic tunnel(Ma=2).The results of schlieren and pressure measurement show that when plasma aerodynamic actuation is applied,the positi
描述:
The shockwave induced by surface direct-current(DC) arc discharge is investigated both experimentally and numerically. In the experiment, the shockwave generated by rapid gas heating is clearly observed from Schlieren images. The peak velocity of the shoc