矢量喷流下平尾偏转对飞机气动性能的影响  

Experimental Investigation on Effect of Horizontal Tail Deflectionon Aerodynamic Characteristics of Aircraft under Vectoring Jet

作　　者：王延奎[1] 邓学蓥[1] 张祖庚[2] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系 [2]沈阳空气动力研究所

出　　处：《北京航空航天大学学报》2003年第2期156-160,共5页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：通过系列参数试验 ,研究有、无矢量喷流作用下飞机平尾偏转对飞机气动特性、操纵特性以及飞机绕流 矢量喷流之间干扰特性的影响 .实验结果表明 :在亚音速中小迎角下 ,有、无矢量喷流时平尾偏转并不影响飞机的纵向静稳定性 ,只是改变飞机的零升力矩系数mz0 和零升力迎角α0 ,但平尾偏转可以较大幅度地改善前体机翼的绕流形态 ,减缓机翼涡及边条涡的破裂 .此外当飞机处于失速状态时 ,矢量喷流对于涡破裂失速流动表现出强烈的干扰作用 ,对飞机的气动特性产生了较大的影响 ,其干扰区域不仅局限于飞机后体 ,而且还延伸至前机体 ,该有利气动干扰量可以达到飞机气动力的 1 0Thrust vectoring is one of the advanced technologies in the design of 4th generation fighters to provide high maneuverability and agility. The effect of horizontal tail deflection on aerodynamic characteristics of aircraft with or without vectoring jet was investigated experimentally in a FL 1wind tunnel, as a function of testing parameters such as ,δ j,α,Ma . Attention was focused on the influence of vectoring jet and the interaction between the vectoring jet and the mainflows around the forebody and afterbody of a modern fighter. It was found that (1) the deflection of the horizontal tail doesn't affect the static stability of the aircraft with or without vectoring jet except the change of m z0 and α 0. (2) Whereas the flow patterns over the wing can be changed greatly, improving the vortices flows and aerodynamic characteristics of the aircraft via the deflection of the horizontal tail. (3) In addition, vectoring jet can influence the vortex burst flow at high attack angle greatly on the afterbody or extending to the foreboy with 10% increment of the lift.

关 键 词：矢量喷流 平尾偏转 飞机 气动性能 影响 喷流干扰 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]