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.
QIAN Guangping
,
LIU Peiqing
,
YANG Shipu
,
DANG Yabin
. A Comprehensive Study on Wingtip Devices in Large Civil Aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012
, (4)
: 634
-639
.
DOI: CNKI:11-1929/V.20111125.1301.003
[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