为了研究等离子体环量控制对翼型的影响特性, 采用基于唯象学的等离子体气动激励数学模型和二维雷诺平均N-S方程, 选取NCCR 1510-7067N环量控制翼型, 数值模拟后缘半径对升力和效费比的影响规律, 并进行优化。设计最佳后缘半径模型进行低速风洞实验, 获得迎角-4°~12°, 速度6, 10, 15 m/s下的压力分布和升力特性。研究表明: 后缘半径过大或过小都不利于Coanda效应的产生, 确定最佳后缘半径与弦长的比值为0048, 效费比97.69。低雷诺数下, 随着迎角的增加, 出现了层流长泡分离和短泡分离, 等离子体射流不仅改善了尾部流场, 还通过环量增加抑制层流分离, 提高了升力。

In order to study the aerodynamics of the airfoil based on plasma circulation control, the Reynolds average N-S equation and mathematics model of plasma excitation based on phenomenology method are used, and the change characteristics of lift affected by the trailing radius are simulated, the optimum radius is determined. Through the low speed wind, the experiment is conducted at the angle of attack of -4° to 12°, and at the speed of 6 m/s, 10 m/s, 15 m/s. The pressure distribution and lift coefficient are obtained. The results of the simulation and experiment show: it is unfavorable for the formation of Coanda effect with too large trailing radius or too small trailing radius, and the optimum ratio of radius and wing chord is 0.048, with the efficiency-cost ratio up to 97.69. The laminar separation of long bubble and short bubble appears with the increase of the angle of attack at low Reynolds number. The influences of plasma jet not only include the tail flow field, but also include improving laminar separation based on the increased circulation, and increasing the lift.