基于网格吸附插值法的不规则尾流场构建方法
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摘要
尾流模型的构建对于尾流遭遇情形下的飞行动力学研究具有重要意义。针对远距尾流的振荡发散特点结合正弦扰动特性构建尾流的长波振荡模型,分析不同幅值参数下尾流场速度参数,提出网格吸附法以解决坐标变换后排列不规则问题。通过与其他插值算法对比,结果表明网格吸附法在标点密度达到拐点的情况下插值速度最快,精度符合要求,效率最高。最后,构建了前机的不规则尾流场。
The construction of wake flow field model is significant for the study of flight dynamics in case of wake.By combining the divergent characteristics of the long distance wake and sinusoidal perturbation charactoristic the long wave oscillation model of the wake is contructed.Velocity parameters of wake flow field with different amplitude parameters are analyzed,and the grid adsorption method is proposed to solve the irregular problem arrayed after coordinate transformation.Compared with other dimensional interpolation algorithms,validation results show that the interpolation of grid adsorption method is fastest when the punctuation density reaches the inflection point,and the precision meet the requirements,causing the highest efficiency.In the end,the irregular wake field of the front plane is constructed.
The construction of wake flow field model is significant for the study of flight dynamics in case of wake.By combining the divergent characteristics of the long distance wake and sinusoidal perturbation charactoristic the long wave oscillation model of the wake is contructed.Velocity parameters of wake flow field with different amplitude parameters are analyzed,and the grid adsorption method is proposed to solve the irregular problem arrayed after coordinate transformation.Compared with other dimensional interpolation algorithms,validation results show that the interpolation of grid adsorption method is fastest when the punctuation density reaches the inflection point,and the precision meet the requirements,causing the highest efficiency.In the end,the irregular wake field of the front plane is constructed.
引文
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[2]ROSSOW V J.Lift-generated vortex wakes of subsonic transport aircraft[R].Progress in Aerospace Sciences,1999,35:507-660.
[3]GERZ T,HOLZAPFEL F,DARRACQ D.Commercial aircraft wake vortices[J].Progress in Aerospace Sciences,2002,38(3):181-208.
[4]CROW S C.Stability theory for a pair of trailing vortices[J].A-merican Institute of Aeronautics and Astronautics Journal,1970,8(12):2172-2179.
[5]DELISI D P,GREENE G C,ROBINS R E,et al.Aircraft wake vortex core size measurements[R].AIAA-2003-3811,2003.
[6]JACQUIN L,FABRE D,GEFFROY P,et al.The properties of a transport aircraft wake in the extended near field:an experimental study[R].AIAA-2001-1038,2001.
[7]PROCTOR F H,HAMILTON D W,HAN J.Wake vortex transport and decay in ground effect:vortex linking with the ground[R].AIAA-2000-0757,2000.
[8]李健兵,王雪松,王涛.基于马蹄涡模型的飞机尾流介电常数分布的快速建模方法[J].航空学报,2009,30(7):1214-1218.LI J B,WANG X S,WANG T.Rapid modeling of distribution of aircraft wake dielectric constant based on horse-shoe vortex model[J].Acta Aeronautica et Astronautica Sinica,2009,30(7):1214-1218.
[9]李大伟,王宏伦.自动空中加油阶段加油机尾涡流场建模与仿真[J].北京航空航天大学学报,2010,36(7):776-780.LI D W,WANG H L.Wake vortex effect modeling and simulation in automated aerial refueling[J].Journal of Beijing University of Aeronautics and Astronautics,2010,36(7):776-780.
[10]魏志强.尾涡流场及安全间隔的建模与仿真计算研究[D].天津:中国民航大学,2008.WEI Z Q.Modeling and simulation of flow field of wake vortex and safety interval[D].Tianjin:Civil Aviation University of China,2008.
[11]MEISCHNER P,BAUMANN R,HOLLER H,et al.Eddy dissipation rates in thunderstorms estimated by Doppler radar in relation to aircraft in situ measurements[J].Journal of Atmospheric and Oceanic Technology,2001,18(10):1609-1627.
[12]FRECH M,HOLZAPFEL F,TAFFERNER A,et al.Highresolution weather data base for the terminal area of Frankfurt airport[J].Journal of Applied Meteorology and Climatology,2007,46(11):1913-1932.