摘要
旋翼翼型经常工作在大迎角来流条件下,流动分离普遍存在。通过在具有分离流动的翼型表面施加零质量射流控制,可以实现对流动分离的抑制,达到增升减阻、推迟失速的目的。本文通过对某旋翼翼型的流动控制的计算,采用数值模拟方法研究了零质量射流主动流动控制机理,并对影响零质量射流控制效果的射流喷角、动量系数和无量纲频率三个控制参数进行了分析比较,得出了一些有意义的结论。
The rotor airfoil often works on the large angle of attack,so the flow separation is very usual.By using the synthetic jet on the airfoil,the separation can be controlled to gain the enhanced lift and the delayed stall angle.In this paper,the control mechanism of the synthetic jet is studied by using numerical simulation method.Then the key control parameter study is also carried out to show the effects of jet angle,momentum coefficient and jet frequency.
出处
《直升机技术》
2010年第1期15-20,共6页
Helicopter Technique
关键词
翼型
零质量射流
控制机理
控制参数
airfoil
synthetic jet
control mechanism
control parameter
