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

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.