新型等离子体激励器对流动分离点控制

在西北工业大学低湍流度风洞中采用新型等离子激励器对NACA0015翼型进行表面流动分离点的控制实验。实验风速为20m／s和35m／s，迎角为0°～16°。并参照压力分布的实验结果对流动控制的效果进行了对比分析。结果表明：翼型表面的气流分离点只要落在等离子体激励所形成的激励区内，分离点都会被推迟到靠近等离子体激励器的最末端电极处。证明等离子激励器能够对翼型表面的分离点进行有效控制。

Flow separation point control by new plasma actuator

Flow separation point control test of airfoil NACA0015 surface by a new plasma ac- tuator is performed in a low turbulence wind tunnel mounted at Northwestern Polytechnical Uni- versity. The wind speed is 35m/s and 20m/s respectively, the attack angle of airfoil changes from 0° to 16°. Flow-control effects are analyzed by comparing with the experimental data of pressure distribution. Experimental results indicate that, as long as the flow separation point is located in the excitation region by the plasma actuator, it will be pushed to the place near the last electrode of the plasma actuator. This proves that new plasma actuator can work effectively on flow separa- tion point control of airfoil surface.