中文摘要：

以减弱超声速飞机头部和进气道调节锥的激波强度为背景,开展了等离子体气动激励控制圆锥激波实验,通过纹影显示以及壁面压力测量来研究圆锥激波形态和激波强度变化的规律。结果表明：当激励电压幅值分别为600V,800V,1 000V时,等离子体气动激励使圆锥激波变为2道激波,激波角度分别增大7.3°、13.2°、18.9°,锥体头部壁面总压分别增大6.52%、8.17%、9.52%,表征总压损失减小,验证了等离子体气动激励可以有效减弱超声速飞机头部和进气道调节锥圆锥激波强度。

英文摘要：

In order to weaken conical shock strength around the aircraft head and the inlet adjustment 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 actuation voltage is 600V, 800V, and 1000V respectively, the results show that when plasma aerodynamic actuation 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% accordingly. So, the fact that conical shock strength can be weakened by plasma aerodynamic actuation is verified.