前体涡诱导双极限环摇滚流动特性的实验研究  

Experimental investigation on flow characteristics during double limit cycle oscillation induced by forebody vortex

作　　者：荣臻[1] 邓学蓥[1] 王兵[1] 马宝峰[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《实验流体力学》2010年第3期19-24,共6页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金资助项目(10432020;10872019;10702004)

摘　　要：通过摇滚/PIV/压力同步测量实验,对翼身组合体前体涡诱导的双极限环摇滚过程中流动特性及演化规律进行了系统的研究,并分析了前体涡诱导翼-身组合体双极限环摇滚的流动机理。实验结果表明,前体涡与机翼翼面流动的相互作用使模型在正负滚转相位处分别出现极限环摇滚运动;正负滚转相位过渡是模型运动惯性与气动力共同作用的结果。The double limit cycle oscillation phenomenon of wing-body configuration at high angle of attack was investigated.Through the experimental study of the flow characteristics by the synchronous measurement and control technique of wing rock/PIV/dynamic pressure,the flow mechanics of the rolling motion induced by forebody vortex was analyzed.The obtained test results demonstrated that the model was in the process of double limit cycle oscillation at each angle side driven by the forebody vortex interacted with wing surfaces;the transition from one side to the other was the effect of inertia of model and aerodynamics.

关 键 词：机翼摇滚 前体涡 PIV 动态测压 翼-身组合体 

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]