飞翼布局低速支撑干扰及局部外形畸变影响数值模拟
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摘要
飞翼布局具有气动效率高、隐身性能好的优点,是未来军民用飞机的重要发展方向。该类布局模型风洞试验尾撑、腹撑及背撑等支撑形式的干扰量及由此带来的模型局部外形畸变影响较为复杂,目前还没有通用的支撑方案和试验修正方法。采用CFD数值模拟方法,分别对某小展弦比飞翼布局标模低速尾撑支杆干扰和尾部外形畸变影响进行了研究,结果表明:在常用角度范围内,所使用的数值模拟方法是可靠的,可用于风洞试验支撑方案的评估及支撑干扰的修正;对纵向特性,尾撑支杆干扰量和尾部外形畸变影响量相对全量较小;对横航向特性,尾撑支杆干扰量基本可忽略,尾部外形畸变影响量与全量相当。
The flying wing configuration shows high aerodynamic efficiency and nice stealth performance.It represents the future military and civil aircraft development direction.The support interference and local shape deformation effect in the wind tunnel test are extremely complex.There are no general support program and correction method for the flying wing configuration test in the wind tunnel.This paper calculated the sting interference and after-body deformation effect on a calibration model of the small aspect ratio flying wing by numerical simulation method.By comparing with the test results,the numerical simulation results are found to be reasonable and the method is proved to be reliable.This method can be used in support program evaluation and support interference correction for the wind tunnel test.The longitudinal components of force or moment of the sting interference and after-body deformation effect are small compared to the longitudinal components themselves.The lateral-directional components of force or moment of the sting interference can be ignored.The lateral-directional components of force or moment of the after-body deformation effect and the lateral-directional components themselves are of the same order of magnitude.
The flying wing configuration shows high aerodynamic efficiency and nice stealth performance.It represents the future military and civil aircraft development direction.The support interference and local shape deformation effect in the wind tunnel test are extremely complex.There are no general support program and correction method for the flying wing configuration test in the wind tunnel.This paper calculated the sting interference and after-body deformation effect on a calibration model of the small aspect ratio flying wing by numerical simulation method.By comparing with the test results,the numerical simulation results are found to be reasonable and the method is proved to be reliable.This method can be used in support program evaluation and support interference correction for the wind tunnel test.The longitudinal components of force or moment of the sting interference and after-body deformation effect are small compared to the longitudinal components themselves.The lateral-directional components of force or moment of the sting interference can be ignored.The lateral-directional components of force or moment of the after-body deformation effect and the lateral-directional components themselves are of the same order of magnitude.
引文
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[2]Petterson K.CFD analysis of the low-speed aerodynamic characteristics of a UCAV[R].AIAA-2006-1259,2006.
[3]McParlin S C,Bruce R J,Hepworth A G,et al.Low speed wind tunnel tests on the 1303UCAV concept[R].AIAA-2006-2985,2006.
[4]Petterson K.Low-speed aerodynamic and flowfield characteristics of a UCAV[R].AIAA-2006-2986,2006.
[5]Woolvin S J.A conceptual design study of the 1303 UCAVconfiguration[R].AIAA-2006-2991,2006.
[6]Arthur M T,Petterson K.A computational study of the lowspeed flow over the 1303UCAV configuration[R].AIAA-2007-4568,2007.
[7]Loser T,Vicroy D,Schütte A.SACCON static wind tunnel tests at DNW-NWB and 14′×22′NASA LaRC[R].AIAA-2010-4393,2010.
[8]Vicroy D,Loser T.SACCON dynamic wind tunnel tests at DNW-NWB and 14′×22′NASA LaRC[R].AIAA-2010-4394,2010.
[9]Gilliott A.Static and dynamic SACCON PIV tests,part I:forward flowfield[R].AIAA-2010-4395,2010.
[10]Konrath R,Roosenboom E,Schr9der A,et al.Static and dynamic SACCON PIV tests,part II:aft flow field[R].AIAA-2010-4396,2010.
[11]Coton F,Mat S,Galbraith R.Low speed wind tunnel characterization of the VFE-2 wing[R].AIAA-2008-0382,2008.
[12]Fritz W.Numerical simulation of the peculiar subsonic flowfield about the VFE-2delta wing with rounded leading edge[R].AIAA-2008-0393,2008.
[13]Carter M B,Dan D Vicroy.Blended-wing-body transonic aerodynamics:summary of ground tests and sample results[R].AIAA-2009-935,2009.
[14]Vicroy D D.Bended-wing-body low-speed flight dynamics:summary of ground tests and sample results[R].AIAA-2009-933,2009.
[15]Liebeck R H.Design of the blended-wing-body subsonic transport[J].Jouranl of Aircraft,2004,41(1):10-25.
[16]Qin N,Vavalle A,Le Moigne A,et al.Aerodynamic studies for blended wing body aircraft[R].AIAA-2002-5448,2002.
[17]程厚梅.风洞实验干扰与修正[M].北京:国防工业出版社,2003.
[18]王勋年.低速风洞试验[M].北京:国防工业出版社,2002.
[19]Carey G F,Stagg A K,Cline D D.Implementing aparabolized Navier-Stokes flow solver on massively parallel,scalable computer systems[C]//Proc of the 7th SIAM Conf on Parallel Processing for Scientific Commuting.1990.
[20]Kim S,Alonso J J,Jameson A.Mufti-element high-lift configuration design optimization using viscous continuous adjoint method[J].Journal of Aircraft,2004,41(5):1082-1097.
[21]Vav Muijden J.CFD support to wind tunnel experiments[C]//European Wind Tunnel Association 2nd Joint Workshop.Farnborough,2006.
[22]Mouton S.Numerical investigations of model support interference in subsonic and transonic wind tunnels[R].ONERA,2007.
[23]李林,马超,王立新.小展弦比飞翼布局飞机稳定特性[J].航空学报,2007,28(6):1312-1317.Li L,Ma C,Wang L X.Stability features of low aspect ratio flying wings[J].Acta Aeronautica et Astronautica Sinica,2007,28(6):1312-1317.
[24]金玲,刘李涛,祝明红.小展弦比飞翼标模尾部畸变影响试验研究[J].空气动力学学报,2016,34(1):119-124.Jin L,Liu L T,Zhu M H,et al.Study on the distortion effect of flying wing in low speed wind tunnel[J].Acta Aerodynamica Sinica,2016,34(1):119-124.
[25]衣秉立,曾凯,王世红.飞翼布局高速风洞尾支干扰试验修正技术研究[J].空气动力学学报,2016,34(1):98-106.Yi B L,Zeng K,Wang S H.Investigation on the interference correction of flying wing aircraft rear sting support in high speed wind tunnel test[J].Acta Aerodynamica Sinica,2016,34(1):98-106.
[26]王勋年,祝明红,孙传宝.低速大迎角尾撑支架干扰试验研究[J].实验流体力学,2007,21(2):8-12.Wang X N,Zhu M H,Sun C B.Investigation on the interference of rear sting supports at high angle of attack in low speed wind-tunnel[J].Journal of Experiments in Fluid Mechanics,2007,21(2):8-12.