大型飞机襟翼吹气增升风洞试验  

Lift enhancement wind tunnel test with flap blowing for large aircraft

作　　者：王万波[1,2] 姜裕标[2] 黄勇[3] 张鑫[1,2] 魏然[2] WANG Wanbo;JIANG Yubiao;HUANG Yong;ZHANG Xin;WEI Ran(State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Low Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,绵阳621000 [2]中国空气动力研究与发展中心低速空气动力研究所,绵阳621000 [3]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《航空学报》2023年第13期68-78,共11页Acta Aeronautica et Astronautica Sinica

摘　　要：襟翼吹气增升技术可以有效提升大型飞机升力,近年来受到越来越多的关注。为改善某型飞机起降性能,在FL-14风洞开展了襟翼吹气增升风洞试验,采用流量控制单元进行内襟翼和外襟翼流量的测量与控制,采用外式空气桥消除供气管路对天平测力的影响。通过空气桥影响试验分析了压力、温度、流量对天平载荷的影响,通过风洞试验研究了动量系数、襟翼偏角对增升效果的影响规律,通过荧光丝线法显示了施加吹气控制前后的表面流场。试验结果表明:施加吹气控制后升力显著增加,升力增加量随着动量系数的增加而增加,升力系数最大增加1.15;襟翼偏角为30°/22.5°时,失速迎角随着动量系数的增加略有增加;襟翼偏角更大时,失速迎角随着动量系数的增加先增加后减小然后再增加;升力增量正比于动量系数的自然对数,随着襟翼偏角的增加,拟合曲线的斜率和截距都增加。The lift of large aircraft can be effectively enhanced with the technology of flap blowing,attracting extensive research and attention in recent years.To improve the take-off and landing performance of a certain type of aircraft,we conduct the flap blowing test in the FL-14 wind tunnel.The two-channel mass flow control unit is used to measure and control the flow of the inboard and outboard flap,and the external air bridge is adopted to eliminate the influence of the air supply pipeline on the force balance measurement.The effect of pressure,temperature and flow rate on the balance load and that of momentum coefficient and flap deflection angle on the lift are studied through the air bridge test and the wind tunnel test,respectively.The surface flow field is visualized with fluorescent tufts.The test results show that the lift increases significantly with flap blowing,and the increment of the lift coefficient increases with the mo⁃ment coefficient,with the maximum increment being 1.15.The stall angle of attack increases slightly with the momen⁃tum coefficient at the flap deflection angle of 30°/22.5°.Larger flap deflection angles firstly increase the stall angle of attack and then decrease and finally increase with the increasing momentum coefficient.Lift increment is proportional to the natural logarithm of the momentum coefficient,while both the slope and intercept of the fitting curve increase with the growing flap deflection angle.

关 键 词：襟翼吹气 流动控制 增升 风洞试验 大型飞机 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]