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针对大迎角状态下,流动绕过顶角为20°的圆锥-圆柱组合体模型产生的一对不对称分离涡,通过等离子体激励器对其进行主动控制,并对控制过程机理进行了分析。实验在实验段为3.0 m×1.6 m的低湍流风洞中进行,实验攻角是45°。基于圆锥体底部直径的雷诺数为50 000。等离子激励器为一对,分别位于实验模型顶部左右两侧,通过频率为10 Hz的占空循环调节,交替对流动产生扰动。实验数据表明,当带有占空循环的激励作用时,分离涡的变化成周期性趋势,并在两个相似于双稳态分离涡型态之间过渡。实验结果表明,当左右激励器在一个占空循环周期中交替开启时间相等时,几乎消除了原有不对称分离涡产生的侧力,实现对不对称分离涡稳定性的控制。
Aiming at the high angle-of-attack state, a pair of asymmetric separation vortexes generated by the cone-cylinder combination model bypassing a vertex angle of 20 ° are flowed and controlled by the plasma actuator. The mechanism of the control process is also analyzed . The experiment was carried out in a low turbulence wind tunnel with an experimental section of 3.0 m × 1.6 m with an experimental angle of attack of 45 °. The Reynolds number is 50 000 based on the cone base diameter. The plasma actuator is a pair, located on the left and right sides of the top of the experimental model, respectively, and is regulated by a duty cycle of 10 Hz to alternately perturb the flow. The experimental data show that the separation vortex changes into a periodic trend with a duty cycle excitation and transitions between two bistable separation vortex patterns. The experimental results show that when the right and left exciters turn on alternately for a duty cycle, the side force generated by the original asymmetric separation vortex is almost eliminated, and the stability of the asymmetric separation vortex is controlled.