双三角机翼前缘涡襟翼的试验研究  

Experimental study of the leading edge vortex-flap of double-delta wing

作　　者：刘铁中[1,2] 王晋军[1] 何宏伟[2] 潘枞[1] 

机构地区：[1]北京航空航天大学,北京100083 [2]中国航空工业空气动力研究院,哈尔滨150001

出　　处：《实验流体力学》2011年第3期6-9,共4页Journal of Experiments in Fluid Mechanics

摘　　要：通过风洞试验对双三角翼的内涡襟翼及外涡襟翼进行了研究。探讨了影响涡襟翼效率的各种因素及其规律,其中包括机翼前缘区状态、涡襟翼形状、涡襟翼偏度、内、外涡襟翼的搭配以及后缘襟翼效率等。尤其是根据内外翼涡场的不同研究了复合平面形状机翼内涡襟翼与外涡襟翼设计上的特点,为设计双三角翼的涡襟翼提供了参考数据。研究结果表明,正确设计前缘涡襟翼与后缘襟翼可以优化大后掠双三角机翼的低速性能。A wind tunnel experiment was conducted to investigate the inner-vortex-flap and outer-vortex-flap of double-delta wing. Various factors affecting the efficiency of vortex-flap,including the state of leading-edge wing, the shape of vortex-flap, the skew of vortex-flap, the combination of inner-vortex-flap and outer-vortex-flap, and the efficiency of trailing edge flap were discussed. Especially, in the light of the difference between the vortex field of inner-vortex- flap and outer-vortex-flap, the design features of inner-vortex-flap and outer-vortex-flap of multiple planform shape wing have been analyzed, which provide a reference for the design of vortexflap of double-delta wing. The results show that proper design of the leading edge vortex-flaps and trailing edge flaps can optimize the low-speed performance of large sweep double-delta wing.

关 键 词：风洞试验 涡襟翼 复合平面形状机翼 前缘吸力恢复 升阻比 

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] V211.74