等离子体气动激励改善增升装置气动性能的试验

发布时间：2018-04-08 09:25

本文选题：增升装置　切入点：等离子体　出处：《航空学报》2016年08期

【摘要】：针对流动分离导致飞机增升装置气动性能下降的问题,进行了脉冲等离子体气动激励抑制增升装置流动分离的试验。研究了等离子体气动激励的频率、占空比及激励位置等参数对流动控制效果的影响。研究结果表明:等离子体气动激励通过加速近壁面附面层,增强附面层内的能量掺混,可有效抑制主翼和襟翼表面的流动分离,改善增升装置气动性能。在主翼前缘施加激励,可有效控制主翼表面大迎角下的失速分离,最大升力系数增大18.1%、临界失速攻角提高4°;在襟翼前缘施加激励,可有效抑制襟翼表面的流动分离,显著减小阻力,在4°迎角下,将试验模型阻力系数减小了28.7%,升力系数提高了7.1%。占空比对控制效果有较大影响,当占空比为10%~30%时,激励的非定常性更强,控制效果最好;占空比为50%的控制效果次之,占空比为100%时的控制效果最差。来流速度越高,逆压梯度越大,流动分离更难被抑制,控制效果也变差。该研究为在增升装置上应用等离子体流动控制技术提供了理论和方法的基础。
[Abstract]:In order to solve the problem that the aerodynamic performance of the aircraft booster device is decreased due to the flow separation, the experiment of suppressing the flow separation by the pulsed plasma pneumatic excitation is carried out.The influence of the frequency, duty cycle and excitation position of plasma aerodynamic excitation on the flow control effect is studied.The results show that the plasma aerodynamic excitation can effectively restrain the flow separation of the main wing and flap surface and improve the aerodynamic performance of the lifting device by accelerating the near wall boundary layer and enhancing the energy mixing in the boundary layer.The stall separation at high angle of attack on the front edge of the main wing can be effectively controlled, the maximum lift coefficient is increased by 18.1, the critical stall angle of attack is increased by 4 掳, and the flow separation on the flap surface can be effectively restrained by applying the excitation at the leading edge of the flap.At the angle of attack of 4 掳, the resistance coefficient of the test model is reduced by 28.7and the lift coefficient is increased by 7.1.Duty cycle ratio has great influence on the control effect. When duty cycle ratio is 10 ~ 30, the unsteadiness of excitation is stronger, the control effect is the best, the control effect of duty cycle is 50%, and the control effect is the worst when duty cycle is 100.The higher the flow rate, the greater the reverse pressure gradient, the more difficult to suppress the flow separation, and the worse the control effect.This study provides a theoretical and methodological basis for the application of plasma flow control technology in the riser.
【作者单位】：空军工程大学航空航天工程学院;西北工业大学航空学院;
【基金】：国家自然科学基金(51207169,51276197,61503302) 中国博士后科学基金(2014M562446) 陕西省自然科学基金(2015JM1001)~~
【分类号】：V211.7

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