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.