采用TRIP3.0模拟CHN-T1模型气动特性
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摘要
采用TRIP3.0软件平台(TRIsonic Platform version 3.0),对第一届航空CFD(Computational Fluid Dynamics)可信度研讨会组委会提供的运输机标模构型(CHiNa-Transport,CHN-T1)进行了流动数值模拟。本文采用粗、中、细三套网格及百亿极细网格进行了网格收敛性研究;采用相应网格分别从气动特性、压力系数分布曲线、表面流态三个方面分析,研究了支撑装置、机翼静弹性变形以及雷诺数效应对CHN-T1构型气动特性的影响。数值模拟结果与试验结果有良好的一致性。数值模拟得到了网格收敛结果;支撑装置对力矩特性影响较大;机翼静弹性变形对气动特性影响较小;雷诺数效应对气动力特性影响较大。
Based on the TRIsonic Platform Version 3.0(TRIP3.0)software,the flow over CHiNa-Transport(CHN-T1)configuration supplied by the committee of 1 st Aeronautic CFD Credibility Workshop,is simulated.The grid convergence is studied by the coarse,medium,fine meshes and the extremely fine one with ten billion grid points.The influence of the tail support,static aeroelasticity of the wing and the Reynolds number effect on the aerodynamic characteristics is investigated by suitable grids.Aerodynamic force coefficient,pressure distributions,and flow patterns on the surface are analyzed.The numerical results agree well with the experimental data.Grid refinement leads to convergence numerical results.It is demonstrated that the tail support has dramatic influence on the moment.The static aeroelasticity of the wing has little influence on the aerodynamic characteristics and Reynolds number effect has obvious influence on the aerodynamic force coefficient.
Based on the TRIsonic Platform Version 3.0(TRIP3.0)software,the flow over CHiNa-Transport(CHN-T1)configuration supplied by the committee of 1 st Aeronautic CFD Credibility Workshop,is simulated.The grid convergence is studied by the coarse,medium,fine meshes and the extremely fine one with ten billion grid points.The influence of the tail support,static aeroelasticity of the wing and the Reynolds number effect on the aerodynamic characteristics is investigated by suitable grids.Aerodynamic force coefficient,pressure distributions,and flow patterns on the surface are analyzed.The numerical results agree well with the experimental data.Grid refinement leads to convergence numerical results.It is demonstrated that the tail support has dramatic influence on the moment.The static aeroelasticity of the wing has little influence on the aerodynamic characteristics and Reynolds number effect has obvious influence on the aerodynamic force coefficient.
引文
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[21]YOON S,Jameson A.Lower-upper symmetric Gauss-Sediel method for the Euler and Navier-Stokes equation[R].AIAAJournal,1988,26(9):1025-1026.
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[23]VASSBERG J C,TINOCO E N,Mani M,et al.Summary of the Fourth AIAA CFD Drag prediction workshop:AIAA-2010-4547[R].Reston:AIAA,2010.
[24]李伟,孟德虹,洪俊武,等.网格拓扑对DLR-F6构型数值模拟影响[J].航空学报,2017,38(2):120177.LI W,Meng D H,Hong J W,et al.Numerical study of mesh topology on DLR-F6configuration[J].Acta Aeronautica et Astronautica Sinica,2017,38(2):120177.(in Chinese)
[25]TINOCO E N.Drag prediction with the Zeus/CFL3Dsystem:AIAA-2004-0552[R].Reston:AIAA,2004.
[2]HAASE W.ECARP-European computational aerodynamics research project:validation of CFD codes and assessment of turbulence models[R].Friedrich Vieweg&Sohn Verlagsgesellschaft mbH,Stuttgart,Germany,1997.
[3]LEVY D W,ZICKUHR T,VASSBERG J C,et al.Summary of data from the first AIAA CFD drag prediction workshop:AIAA 2002-0841[R].Reston:AIAA,2002.
[4]LAFLIN K R,KLAUSMEYER S M,ZICKUHR T,et al.Data summary from the second AIAA computational fluid dynamics drag prediction workshop[J].Journal of Aircraft,2005,42(9):1165-1178.
[5]VASSBERG J C,TINOCO E N,MANI M,et al.Abridged Summary of the third AIAA CFD drag prediction workshop[J].Journal of Aircraft,2008,45(6):781-798.
[6]VASSBERG J C,TINOCO E N,MANI M,et al.Summary of the fourth AIAA CFD drag prediction workshop:AIAA 2010-4547[R].Reston:AIAA,2010.
[7]LEVY D W,LAFLIN K R,TINOCO E N,et al.Summary of data from the fifth AIAA CFD drag prediction workshop:AIAA 2013-0046[R].Reston:AIAA,2013.
[8]RUMSEY C L,LONG M,STUEVER R A.Summary of the first AIAA CFD high lift prediction workshop(invited):AIAA2011-939[R].Reston:AIAA,2011.
[9]阎超,席柯,袁武,等.DPW系列会议述评与思考[J].力学进展,2011,41(6):776-784.YAN C,XI K,YUAN W,et al.Review of the drag prediction workshop series[J].Advances in Mechanics,2011,41(6):776-784.(in Chinese).
[10]张耀冰,邓有奇,吴晓军,等.DLR-F6翼身组合体数值计算[J].力学进展,2011,41(6):776-784.ZHANG Y B,DENG Y Q,WU X J,et al.Drag prediction of DLR-F6 using MFlow unstructured mesh solver[J].Acta Aerodynamica Snica,2011,29(2):163-169.(in Chinese).
[11]王运涛,孙岩,孟德虹,等.包含支撑装置和机翼变形的CRM_WB构型气动特性数值模拟[J].航空学报,2017,38(10):121202.WANG Y T,SUN Y,MENG D H,et al.Numerical simulation of aerodynamic characteristics of CRM-WBconfiguration with support system and wing deformation[J].Acta Aeronautica et Astronautica Sinica,2017,38(10):121202.(in Chinese).
[12]王运涛.DPW IV~DPW VI数值模拟技术综述[J].航空学报,2018,39(4):021836.WANG Y T.An overview of DPW IV~DPWVI numerical simulation technology[J].Acta Aeronautica et Astronautica Sinica,2018,39(4):021836(in Chinese).
[13]王运涛,孟德虹,孙岩,等.CRM-WB风洞模型高阶精度数值模拟[J].航空学报,2018,39(4):121642.WANG Y T,MENG D H,SUN Y,et al.High-order numerical simulation of CRM-WB wind tunnel model[J].Acta Aeronautica et Astronautica Sinica,2018,39(4):121642(in Chinese).
[14]余永刚,周铸,黄江涛,等.单通道客机气动标模CHN-T1设计[J].空气动力学学报,2018,36(3):505-513.YU Y G,ZHOU Z,HUANG J T,et al.Aerodynamic design of a standard model CHN-T1for single-aisle passenger aircraft[J].Acta Aerodynamica Sinica,2018,36(3):505-513.(in Chinese)
[15]洪俊武,王运涛.关于组织“第一届航空CFD可信度研讨会---CHN-T1标模CFD可信度研讨会”的通知,附件2:候选模型[EB/OL].http://www.cardc,cn/eReadNews.Asp.?Channelld=2&Classld=6&ld=119,2018-05-10/2019-01-18.
[16]李强,刘大伟,许新,等.CHN-T1标模2.4米风洞气动特性试验研究[J].空气动力学学报,2019,37(2):337-344.doi:10.7638/kqdlxxb-2018.0099.(in Chinese)LI Q,LIU D W,XU X,et al.Experimental study of aerodynamic characteristic of CHN-T1standard model in 2.4m transonic wind tunnel[J].Acta Aerodynamica Sinica,2019,37(2):337-344.
[17]王运涛,洪俊武,孟德虹.湍流模型对梯形翼高升力构型的影响[J].空气动力学学报,2013,31(1):52-55.WANG Y T,HONG J W,MENG D H.The influence of turbulent models to trap wing simulation[J].Acta Aerodynamica Sinica,2013,31(1):52-55.(in Chinese)
[18]王光学,王运涛.TRIP2.0软件湍流模块的开发与确认[J].航空计算技术,2007,37(3):20-23.WANG G X,WANG Y T.Development and validation of turbulence models of TRIP2.0[J].Aeronautical Computing Technique,2007,37(3):20-23.(in Chinese)
[19]王运涛,张玉伦,洪俊武,等.TRIP2.0_SOLVER的开发与应用[J].空气动力学学报,2007,25(2):163-168.WANG Y T,ZHANG Y L,HONG J W,et al.Development and application of TRIP2.0_SOLVER[J].Acta Aerodynamica Sinica,2007,25(2):163-168.(in Chinese)
[20]王运涛,王光学,张玉伦.采用TRIP2.0软件计算DLR_F6构型的阻力[J].空气动力学学报,2009,27(1):108-113.WANG Y T,WANG G X,ZHANG Y L.Drag prediction of DLR-F6 configuration with TRIP2.0 software[J].Acta Aerodynamica Sinica,2009,27(1):108-113.(in Chinese)
[21]YOON S,Jameson A.Lower-upper symmetric Gauss-Sediel method for the Euler and Navier-Stokes equation[R].AIAAJournal,1988,26(9):1025-1026.
[22]VAN LEER B.Towards the ultimate conservation difference scheme II,monoticity and conservation combined in a second order scheme[J].Journal of Computational Physics,1974,14:361-370.
[23]VASSBERG J C,TINOCO E N,Mani M,et al.Summary of the Fourth AIAA CFD Drag prediction workshop:AIAA-2010-4547[R].Reston:AIAA,2010.
[24]李伟,孟德虹,洪俊武,等.网格拓扑对DLR-F6构型数值模拟影响[J].航空学报,2017,38(2):120177.LI W,Meng D H,Hong J W,et al.Numerical study of mesh topology on DLR-F6configuration[J].Acta Aeronautica et Astronautica Sinica,2017,38(2):120177.(in Chinese)
[25]TINOCO E N.Drag prediction with the Zeus/CFL3Dsystem:AIAA-2004-0552[R].Reston:AIAA,2004.