以外加辅助件推迟三角翼上涡破裂的初步水洞实验  

THE WATER TUNNEL TEST OF DELAYING VORTEXBREAKDOWN OVER A DELTA WINGUSING SUPPLEMENTS

作　　者：潘家正[1] 莫家大 吴健民 

机构地区：[1]南京航空学院 [2]美国田纳西州大学

出　　处：《空气动力学学报》1989年第3期344-350,共7页Acta Aerodynamica Sinica

摘　　要：对尖锐前缘、后掠角为60°的大攻角平板三角翼模型进行了水洞实验。利用附加的小辅助件,改变翼面上方的流场,使机翼前缘肌体涡推迟破裂。流动显示表明:在翼面上的适当位置安放圆弧形或三角形导流体,或在翼面上方另加一辅助小三角翼,能使涡破裂推迟的效果得到显著提高。此结果可供推迟涡破裂来改善飞机气动性能的研究工作参考。The test of a flat delta wing with a sharp leading edge and back-swept angle of 60° was performed in water tunnel. The leading edge vortex breakdown can be delayed using supplements to change the flow field over upper surface of the wing.The flow visualization shows: the effects of delay of vortex breakdown can be enhanced if an arc or a triangle guiding object is put on appropri-ate position of upper surface and so is a small supplemental delta wing put over the wing surface.This preliminary result could be provided to research of the problem about the general configuration design of aircraft using the delaying of vortex breakdown.

关 键 词：三角翼 涡破裂 水洞实验 辅助件 

分 类 号：V211.751[航空宇航科学与技术—航空宇航推进理论与工程]