基于等离子体合成射流的飞翼布局模型主动流动控制风洞实验研究

为探究等离子体合成射流对三维模型的流动控制效果和机理，在中等展弦比飞翼布局模型前缘布置等离子体合成射流激励器开展低速风洞实验研究。通过六分量天平测力，考察沿弦向、展向不同分布位置的等离子体合成射流对飞翼模型气动力和气动力矩的作用；采用PIV（Particle Image Velocimetry，粒子图像测速）测量模型表面流场分布，研究等离子体合成射流流动控制机理。结果表明:在飞翼模型单侧布置等离子体合成射流，能够有效改善其气动特性，并能产生附加的滚转力矩，滚转力矩系数变化量最高达到0.009；在飞翼模型左右弦布置等离子体合成射流，能显著增强飞翼模型横向稳定性，滚转力矩系数波动范围减小66.7%。沿弦向，等离子体合成射流位置离前缘越近，控制效果越好，距前缘0mm的激励器控制效果最好；沿展向，布置的等离子体合成射流越多，对模型的升力特性改善作用越明显，布置方式以均布为优。在失速迎角前后，等离子体合成射流的流动控制机理不同:在小迎角下，等离子体合成射流在前缘起到了使转捩提前的作用；在失速迎角附近，则加速了分离区的流动、减小了分离区厚度。

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.