摘要
This study investigates the aerodynamic performance of the NACA 633-421 airfoil and the effectiveness and feasibility of intermittent disturbance flow control methods on laminar separation bubbles(LSBs).It is found that the average velocity and influence range of the synthetic jet actuator increase with the increasing of driving frequency and driving amplitude.LSB occurs at Re=1.0×10^(5),and ruptures atα=6°.But with intermittent disturbance control,the stall angle of attack(AoA)increases while significantly reducing drag.Research shows that although certain disturbance cannot fully recover from LSB stall,decreasing driving amplitude partially restores wing aerodynamic performance,more effectively than increasing driving amplitude.
研究了NACA 633-421翼型的气动性能,以及层流分离泡(Laminar seperation bubble,LSB)间歇扰动流动控制方法的有效性和可行性。研究发现,合成射流激励器的平均速度和影响范围随驱动频率和驱动幅值的增加而增大。LSB会在Re=1.0×10^(5)条件下形成,并且在α=6°时发生破裂造成升力突降。但采用间歇扰动控制后,失速迎角(Angle of attack,AoA)增大,阻力明显减小。研究表明,虽然某些干扰幅值不能完全使机翼升力系数从LSB失速中恢复,但减小驱动幅值比增大合成射流驱动幅值更能部分恢复机翼气动性能,使得机翼的整体气动特性得以保持。
