The wind tunnel test of the active flow control on the flying wing model based on the plasma synthetic jet

To explore the effects and mechanisms of plasma synthetic jet flow control of the 3D model, a wing layout model with medium aspect ratio decorated with plasma synthetic jets on the leading edge is studied by means of low speed wind tunnel tests. The effects of the aerodynamic force and the aerodynamic moment on the airfoil model are investigated by measuring the force of the six component balance and the different distribution positions of the synthetic jet of the plasma. The flow field distribution on the surface of the model measured by PIV(Particle Image Velocimetry) is used to study the mechanism of the plasma jet flow control. Test results show that the unilateral arrangement of the plasma synthetic jet actuator can effectively improve the aerodynamic characteristics of the flying wing model, and can produce an additional roll moment with the variation of the roll moment coefficient reaching 0.009; The lateral stability of the flying wing model can be significantly enhanced by using the plasma synthetic efflux on the left and right side of the flying wing model, and the range of the rolling torque coefficient fluctuation decreases by 66.7%. Along the string, the closer the position of the plasma jet to the leading edg is, the better the control effect is, and the control effect of the exciter at the leading edge is the best. The more the plasma synthesized jet flows along the exhibition are arranged, the more obvious the improvement of the lift characteristics of the model is, and the uniform arrangement is the best. The flow control mechanism of the plasma synthetic jet actuator is different before and after the stall angle of attack. Under the small angle of attack, the synthesis of the plasma jet advances the transition, and near the stall angle of attack, the plasma synthetic jet accelerates the separation of the flow and reduces the separation-zone thick-ness.