摘要
本文对内吹式边界层控制方案的气动力特性进行风洞试验,获得了不同吹气动量系数时的气动力特性,同时对该方案进行计算流体力学(CFD)数值模拟对比研究。为了大幅减少网格数量,数值模拟的吹气边界选择在喷口处代替稳压腔边界,采用变风速的形式改变吹气动量系数。结果表明,数值模拟和风洞试验结果整体趋势吻合较好,计算结果在升力方向上较为乐观,在大吹气动量系数时,起飞状态计算比试验的升力系数大5.7%左右,俯仰力矩系数的误差在3%左右。计算结果还表明,采用高速气流对襟翼边界层进行吹除,增加了襟翼边界层的能量,消除了襟翼的分离,襟翼吹气不仅增加了襟翼上面的负压,由于高速气流的引射作用,主翼面的负压同样大幅增加,进而提高整个翼面的升力;在大迎角时,失速形式仍旧是襟翼失速,而不是头部失速。
A wind tunnel test was made to investigate the aerodynamic characteristics of the airplane with internally blown flaps.The results were obtained according to different jet momentum coefficients and a comparison analysis using CFD technology was made simultaneously.In order to decrease the amount of the grids dramatically,the blowing boundary was set at the nozzle exit instead of the internal of the steady pressure tube and a change of the wind velocity was made to change the jet momentum coefficient.The results obtained by the numerical simulation and the wind tunnel tests were nearly the same,especially in the direction of lift.With large jet momentum,the lift coefficient of CFD results were 5.7%larger than the wind tunnel results,3%for pitching moment.The results also showed that using high speed jet to blow the flap energizes the flow of the boundary layer and prevents the separation of the flap.The blowing jet not only enhanced the negative pressure of the flap,but also increased the negative pressure of the main wing,thus enhancing the lift of the wing simultaneously.Under the large angle of attack,the separation started at the trailing edge of the flap,not the leading edge of the main wing.
作者
温庆
杨康智
彭新春
程志航
Wen Qing;Yang Kangzhi;Peng Xinchun;Cheng Zhihang(AVIC General Huanan Aircraft Industry Co.,Ltd.,Zhuhai 519040,China)
出处
《气动研究与试验》
2024年第5期52-57,共6页
Aerodynamic Research & Experiment
关键词
边界层控制
吹气动量系数
数值模拟
风洞试验
失速形式
boundary layer control
jet momentum coefficient
numerical simulation
wind tunnel tests
stall pattern
