翼尖装置由于其良好的气动特性在航空界得到了广泛应用,然而它也使飞机的颤振及结构重量特性发生了变化。为了探求翼尖装置的综合特性,利用数值模拟方法对大型客机上最先进的3种翼尖装置(融合式、鲨鱼鳍式和阶梯式)进行了气动、颤振及重量3个方面的综合研究。3种翼尖装置减阻效果明显,但同时结构重量亦增加。翼尖装置均降低了机翼颤振速度。研究结果表明:加装翼尖装置后机翼颤振形态取决于翼尖装置的形式。相对于机翼颤振速度,翼尖装置形式对机翼颤振速度的影响是小量(1%~7%),且翼尖装置减阻和机翼压心外移的综合重量增益,为机翼结构设计提供了一定的设计空间。
Wingtip devices are commonly used on aircraft because of their good aerodynamic characteristics.However, the flutter characteristics of the aircraft are changed by the devices, and so is the structural weight.In order to explore the overall performance of the wingtip devices in a large civil aircraft, three kinds of wingtip devices (blended, sharklet, ladder) are studied in terms of aerodymaics, fluttering and weight by numerical simulation.There are obvious benefits from drag reduction by adding any of the three wingtip devices, but the structural weight increases as a result.The flutter velocity of the wing is reduced by adding a wingtip device.The results show that the flutter shape depends on the form of the wingtip device.The effect on the flutter velocity of the wing due to the form of the wingtip device is about 1%-7%, which is relatively small.And the overall weight benefits from drag reduction and the displacement of the pressure center can provide certain weight capa-city for the structural design.
[1] Whitcomb R T.A design approach and selected wind-tunnel results at high subsonic speeds for wingtip mounted winglets.NASA TN D-8260, 1976.
[2] Jiang Y Q.Aircraft winglet design.Beijing:Aviation Industry Press, 2009: 52-182.(in Chinese) 江永泉. 飞机翼梢小翼设计. 北京: 航空工业出版社, 2009: 52-182.
[3] Fang B R.The aerodynamic configuration design of aircraft. Beijing:Aviation Industry Press, 1997:1150-1158.(in Chinese) 方宝瑞.飞机气动布局设计.北京: 航空工业出版社, 1997:1150-1158.
[4] Edwards J W, Schuster D M, Spain C V, et al. MAVRIC flutter model transonic limit cycle oscillation test.AIAA-2001-1291, 2001.
[5] Gatto A, Mattioni F, Friswell M I. Experimental investigation of bistable winglets to enhance wing lift takeoff capability. Journal of Aircraft, 2009, 46(2): 647-655.
[6] Park P S, Rokhsaz K.Effects of winglet rudder on lift-to drag and wake vortex frequency.AIAA-2003-4069, 2003.
[7] Keenan J A, Kuhlman J M.The effects of winglets on low aspect ratio wings at supersonic mach numbers. NASA Contractor Report 4407,1991.
[8] Jones R T, Lasinski T A. Effect of winglets on the induced drag of ideal wing shapes. NASA TM-81230, 1980.
[9] Fu W, Zhao X, Si L.Geometric parameters of winglet for the effect on characteristics of the basic wing.Science Technology and Engineering, 2010,10(14): 3378-3383.(in Chinese) 付伟, 赵旭, 司亮.翼梢小翼几何参数对机翼的气动特性影响研究.科学技术与工程, 2010, 10(14): 3378-3383.
[10] Ruhlin C L.Transonic flutter study of a wind-tunnel model of a supercritical wing with/without winglet.AIAA-1982-721, 1982.
[11] Ruhlin C L, Rauch F J, Waters C.Transonic flutter model study of a supercritical wing and winglet. Journal of Aircraft, 1983, 20(8): 711-716.
[12] Ruhlin C L, Bhatia K G, Nagaraja K S.Effects of winglet on transonic flutter characteristics of a cantilevered twin-engine transport wing model. NASA Technical Paper, 1986.
[13] Kehoe M W. KC-135 winglet flight flutter program. NASA CP-2211,1982:171-188.
[14] AGARD.Numerical unsteady aerodynamics and aeroelastic simulation.AGARD Report R-822,Neuilly-sur-Seine,1998.
[15] Zwaan R J, Prananta B B. Fluid/Structure interaction in numerical aeroelastic simulation.International Journal of Nonlinear-Mechanics, 2002,37: 987-1002.
[16] de Mattos B S, Macedo A P, da Silvafilho D H. Considerations about winglet design.AIAA-2003-3502, 2003.
CJA