二维翼型吹/吸气流动控制试验研究  

Experimental Study on 2D Airfoil Blowing and Suction Flow Control

作　　者：王昊[1,2] 牛中国 蒋甲利[1,2] Wang Hao;Niu Zhongguo;Jiang Jiali(AVIC Aerodynamics Research Institute,Harbin 150001,China;Low Speed High Reynolds Number Aeronautical Key Laboratory,Harbin 150001,China)

机构地区：[1]中国航空工业空气动力研究院,黑龙江哈尔滨150001 [2]低速高雷诺数航空科技重点实验室,黑龙江哈尔滨150001

出　　处：《航空科学技术》2020年第5期56-63,共8页Aeronautical Science & Technology

摘　　要：吹/吸气控制可以有效地对边界层流动进行干预。针对NACA0015翼型,应用吹/吸气流动控制系统在低速风洞进行了不同位置、不同流量的吹/吸气对翼面流动分离控制的试验研究,并采用粒子图像测速(PIV)技术试验的方法分析了翼面流动分离的规律。试验结果表明,吸气控制效果整体优于吹气控制;吹气控制时,在10%c附近进行吹气对翼面流动分离的抑制效果较好,在流量较小时,对模型失速特性的改善不明显,当流量继续增大到一定程度时,对模型失速特性的改善出现较大的改善,但当流量继续增加时,改善效果降低;吸气控制时,在翼型前缘吸气的效果最好,较小流量就可明显提高模型的失速迎角,但当流量增大到一定程度后,对模型失速特性的改善不会随流量的增大而提高。Blowing/suction control can effectively intervene in boundary layer flow.For the NACA0015 airfoil,the blowing/suction flow control system is used to conduct experimental research on the separation and control of airfoil flow at different positions and different flows in the low-speed wind tunnel.The PIV test method is used to analyze the law of flow separation.The test results show that the overall effect of the suction control is better than that of the blowing control.During the blowing control,the effect of suppressing the flow separation of the airfoil by blowing at about 10%C is better.The model stall characteristic is not obvious when the flow rate is small,as the flow rate continues to increase to a certain extent,the improvement of the stall characteristics will be greatly improved,but when the flow rate continues to increase,the improvement effect decreases.When the suction control is performed at the leading edge of the airfoil,the control effect is the best,and a smaller flow can significantly increase the stall angle of attack of the model,but when the flow increases to a certain extent,the improvement of the model’s stall characteristics will not increase with the increase of the flow.

关 键 词：吹/吸气控制 流动分离 流动控制 风洞试验 PIV 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]