飞翼模型纵向气动特性等离子体流动控制试验  

Experiment on longitudinal aerodynamic characteristics of flying wing model with plasma flow control

作　　者：牛中国[1,2] 许相辉 王建锋[1] 蒋甲利[1] 梁华[2] Niu Zhong-Guo;Xu Xiang-Hui;Wang Jian-Feng;Jiang Jia-Li;Liang Hua(Key Laboratory of Low Speed High Reynolds Number Aeronautical,AVIC Aerodynamics Research Institute,Harbin 150001,China;College of Aeronautics and Astronautics Engineering,Air Force Engineering University,Xi’an 710038,China)

机构地区：[1]中国航空工业空气动力研究院,低速高雷诺数航空重点实验室,哈尔滨150001 [2]空军工程大学航空航天工程学院,西安710038

出　　处：《物理学报》2022年第2期167-178,共12页Acta Physica Sinica

摘　　要：为了改善大展弦比飞翼模型纵向操纵性和稳定性,在低速风洞中开展了等离子体流动控制技术的试验研究.采用粒子图像测速技术获取了等离子体对翼面流场的影响.采用静态测力技术获取了等离子体对模型气动力和升降舵舵效的影响.采用虚拟飞行试验技术获取了等离子体对俯仰角和俯仰角速度时间历程的影响.通过对粒子图像测速和测力试验结果的分析表明,等离子体能够抑制翼面流动分离,阻止气动中心前移,改善模型的大迎角纵向气动特性.通过分析不同舵偏角的测力数据,来流风速V=50 m/s时等离子体能够改善飞翼模型大迎角的升降舵舵效,在不同舵偏角时均使模型的最大升力系数提高约0.1、失速迎角推迟4°以上.通过分析虚拟飞行试验结果,等离子体能够将模型的临界俯仰角提高3.6°,能够改善飞翼模型的纵向飞行稳定性和操纵性.Horizontal tail is eliminated from the flying wing layout for improving the low observable and aerodynamic efficiency,resulting in degrading longitudinal maneuverability and fight stability.The low speed wind tunnel test study of improving the longitudinal aerodynamic characteristics of large aspect ratio flying wing model is carried out by using plasma flow control technology.The flying wing model has a leading-edge sweep angle of 34.5° and an aspect ratio of 5.79.The reasons for deteriorating the static maneuverability and stability of the flying wing model and the mechanism of plasma control of the flow field and longitudinal aerodynamic characteristics are studied by particle image velocimetry(PIV) flow visualization and static force measurement test.The control law of plasma control of the flight maneuverability and stability of the flying wing model is studied through flight test.The fact that the flow separation of the outer wing of the flying wing model occurs earlier than the inner wing and the wing is swept back can result in the forward movement of the aerodynamic center and the deterioration of the longitudinal static stability.The shock disturbance induced by plasma can suppress the flow separation of the suction surface,thereby extending the linear section of the lift curve of the model,preventing the aerodynamic center from moving forward,and improving the longitudinal static stability.When the wind speed is 50 m/s,the plasma control improves the horizontal rudder efficiency at a high angle of attack of the flying wing model,increases the maximum lift coefficient of the model by about 0.1,and postpones the stall angle of attack by more than 4° at different rudder angles.The plasma control allows the flying model to follow the command movement better while flying,increases the flying pitch limit angle from 11.5° to 15.1°,reduces the amplitude of longitudinal disturbance motion by 2°,and reduces the oscillation attenuation time from 15 to 8 s,thereby improving the longitudinal flight maneuverabi

关 键 词：等离子体 流动控制 飞翼 风洞试验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]