Experimental Research on Plasma Actuation in Controlling Conical Shock
CHENG Bang-qin
WANG Hao
SUN Quan
HU Wei-bo
CHEN Zhi-min
LI Jun
Abstract：In order to weaken conical shock strength around the aircraft head and the inlet adj ustment cone caused by supersonic flow,the experiment of plasma aerodynamic actuation in controlling conical shock is conducted.Variable laws of conical shock shape and in different excitation voltage conditions are performed by means of optical measurement and wall static pressure measurement.When the amplitude value of actu-ation voltage is 600V,800V,and 1000V respectively,the results show that when plasma aerodynamic ac-tuation conical shock shape is turned into 2 shocks,the shock wave angle is increased by 7.3°,13.2°,18.9° respectively and the cone head wall maximum total pressure is increased by 6.52%,8.17%,and 9.52% ac-cordingly.So,the fact that conical shock strength can be weakened by plasma aerodynamic actuation is verified.
Keywords：supersonic flowflow controlconical shockplasma aerodynamic actuation
Publication Date：2015-01-01
Pages：4( 6-9 )