洞壁对过失速非定常三角翼涡破碎位置的影响  

EFFECT OF TUNNEL WALLS ON VORTEX BREAKDOWN LOCATION OVER DELTA WINGS WITH OSCILLATING IN PITCH TO VERY HIGH ANGLES OF ATTACK

作　　者：张文华[1] 张庆利[1] 周兴奎[1] 

机构地区：[1]南京航空航天大学6系

出　　处：《航空学报》1996年第S1期83-86,共4页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金

摘　　要：在南航低速风洞中用两组后掠角分别为６５°和７０°的三角翼模型进行了过失速非定常涡破碎位置测定实验。各组模型几何相似，展长与风洞宽度之比分别为０．１７５，０．３５和０．７。涡及其破碎点位置由ＴｉＣｌ４烟流显示并由相机记录。实验表明，同样攻角条件下。The effect of the size of a delta wing relative to that of the test section on the vortex breakdown location over a delta wing oscillating in pitch to very high angles of attack was investigated experimentally using flow visualization in wind tunnel in NUAA. The models tested consist of two sets of delta wings having 65° and 70° leading edge sweep.The wings in each set differ from one another in their linear dimensions. The breakdown location, at the same constant angle of attack,moves continuously backward as the wing grows larger.

关 键 词：非定常流 旋涡 破裂 干扰 风洞壁 

分 类 号：V211.15[航空宇航科学与技术—航空宇航推进理论与工程]