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缝道流动参数对多段翼型气动特性非常重要。通常采用改变翼型外形、缝道几何参数组合以及流动主/被动控制来改变缝道流动参数,提高多段翼型的气动性能。在不同的声激励方式下,通过风洞实验的方法研究多段翼型升力特性变化的规律,以探索提高增升效果的新途径。采用NF-3风洞实验,着重研究声源在模型表面的位置及排列方式对翼型升力特性影响的规律,包括单点激励、单排多点激励、多排多点激励、M型多点激励等四种不同的激励方式。结果表明:在GAW-1两段翼型的襟翼上表面加入弱声激励,翼型的升力系数有了一定变化;不同的激励方式对翼型升力系数的影响不同;在研究范围内,单点声激励使翼型的升力系数减小,M型多点声激励使翼型的升力系数少量增加。
Seam flow parameters are important for the aerodynamic characteristics of multi-section airfoils. Usually change the airfoil shape, seam geometry parameters and flow of the main / passive control to change the seam flow parameters to improve the aerodynamic performance of multi-section airfoil. Under different acoustic excitation methods, the wind tunnel experiment was used to study the rule of the lift characteristics of multi-section airfoils to explore a new way to improve the effect of airlift. Using NF-3 wind tunnel experiment, we focus on the study of the influence of sound source on the model surface and its arrangement on the lift characteristics of airfoil, including single point excitation, single row multi-point excitation, multi-row multi-point excitation, Incentives and other four different incentives. The results show that the lift coefficient of the airfoil changes with the weak acoustic excitation on the upper flaps of the GAW-1 airfoil. The influence of different excitation modes on the airfoil lift coefficient is different. Within the scope of the study, Spot excitation reduced the lift coefficient of airfoil and M type multi-point acoustic stimulation increased the lift coefficient of airfoil slightly.