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中文摘要：
通过数值模拟的方法,对合成射流控制NACA 0012大攻角下翼型流动分离的参数进行了研究。结果表明：对于射流出口宽度为翼型弦长的0.5%,翼型在18°～24°攻角下的流场,当合成射流作用在翼型头部1%弦长位置,吹气速度比为1,无量纲激励频率在1附近时,可以达到较好的改善翼型整体气动性能的效果。通过对翼型表面压强系数分布及流场结构进行分析,揭示了合成射流主动流动控制的内在机制。
英文摘要：
In this paper,the method of numerical simulation is used to study the parameters of flow separation of NACA 0012 airfoil at large angle of attack with synthetic jet control.For the flow field under the condition of the angle of attack as 18°～24° and the jet outlet width as 0.5% of airfoil chord,the result shows that it can achieve better effect of improving overall aerodynamic performance of airfoil when the synthetic jet acted on the position of 1% chord of the head of airfoil,the inflatable speed ratio as 1,and the dimensionless excitation frequency near 1.The internal mechanism of synthetic jet active flow control is revealed based on analyzing the distribution of airfoil surface pressure coefficient and the structure of flow field.
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