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为了进一步提高等离子体激励器可控雷诺数,采用测力以及粒子图像测速(PIV)等研究方法,从二维机翼到三维半模,从低雷诺数到高雷诺数,开展了对称布局式介质阻挡放电(DBD)等离子体激励器控制超临界机翼气动特性的试验研究,分析了控制机理,实现了等离子体“虚拟舵面”的功能。结果表明:在雷诺数为2×106的情况下,对称布局式等离子体气动激励能较好地抑制超临界机翼绕流流场分离,使失速迎角推迟2°,最大升力系数提高8.98%。
In order to further improve the controllability Reynolds number of plasma actuator, using the research methods of force measurement and particle image velocimetry (PIV) and so on, from two-dimensional wing to three-dimensional half-mode, from low Reynolds number to high Reynolds number, Dielectric barrier discharge (DBD) plasma actuator experimental study of aerodynamic characteristics of supercritical wing, analysis of the control mechanism, to achieve the plasma “virtual rudder ” function. The results show that under the Reynolds number of 2 × 106, the symmetric distributed plasma aerodynamic excitation can restrain the flow around the supercritical wing better, and the angle of attack is delayed by 2 ° and the maximum lift coefficient is increased by 8.98% .