CHN-T1标模大型低速风洞试验结果相关性分析
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摘要
为满足型号研制的试验数据质量需求,进一步开展CFD验证与确认工作,中国空气动力研究与发展中心建立了大展弦比运输机高低速统一标模体系。为获得可靠风洞试验数据,使用设计加工的第一个运输机标模CHN-T1(1∶6.4,翼展4.667m)在FL-13风洞和DNW-LLF风洞进行了试验。同一构型下,前者试验雷诺数为1.4×10~6～2.5×10~6,后者试验雷诺数为1.4×10~6～3.2×10~6。模型在FL-13风洞中通过TG1801A内式六分量天平与大迎角支撑机构相连,在DNW-LLF风洞中则通过W616天平与尾撑机构相连。两风洞均测量了模型力和力矩。风洞试验数据差异评估包括重复性、气动特性和雷诺数影响。结果对比表明:标模在不同风洞试验中的升力线斜率相差很小;设计升力点附近(Ma=0.78,C_L=0.5)阻力系数相差0.0004,试验数据一致性较好;雷诺数对标模气动特性影响符合预期。
China Aerodynamics Research and Development Center(CARDC)established a uniform large aspect ratio transport aircraft calibration model system for high and low speed wind tunnels to fulfill the data quality requirements of aircraft type development and CFD validation and confirmation.To acquire reliable wind tunnel data,CARDC tested the first self-developed transport calibration model CHN-T1(1∶6.4,4.667 m wing span)in FL-13 wind tunnel and DNW-LLF wind tunnel at chord Reynolds number from 1.4 to 2.5 million in FL-13 wind tunnel and from 1.4 to 3.2 million in DNW-LLF wind tunnel for the same configuration.CHN-T1 model was mounted on a TG1801 Asix-component strain-gauge internal main balance connected to the large angle of attack(AOA)support mechanism in FL-13 wind tunnel and on a W616 internal main balance connected to a sting support in DNW-LLF wind tunnel.Both of the force and moment data were obtained in both facilities.Tunnel to tunnel variations including repeatability,aerodynamic characteristics and Reynolds effect have been assessed.Results comparison shows that slop of lift curve(C_(Lα))varies very little and drag coefficient(C_D)is of a difference of 0.0004 around the design point with Ma=0.78 and lift coefficient(C_L)=0.5.Test data indicates good agreement.Reynolds number effect on CHN-T1 calibration model aerodynamic characteristics follows the expected trends.
China Aerodynamics Research and Development Center(CARDC)established a uniform large aspect ratio transport aircraft calibration model system for high and low speed wind tunnels to fulfill the data quality requirements of aircraft type development and CFD validation and confirmation.To acquire reliable wind tunnel data,CARDC tested the first self-developed transport calibration model CHN-T1(1∶6.4,4.667 m wing span)in FL-13 wind tunnel and DNW-LLF wind tunnel at chord Reynolds number from 1.4 to 2.5 million in FL-13 wind tunnel and from 1.4 to 3.2 million in DNW-LLF wind tunnel for the same configuration.CHN-T1 model was mounted on a TG1801 Asix-component strain-gauge internal main balance connected to the large angle of attack(AOA)support mechanism in FL-13 wind tunnel and on a W616 internal main balance connected to a sting support in DNW-LLF wind tunnel.Both of the force and moment data were obtained in both facilities.Tunnel to tunnel variations including repeatability,aerodynamic characteristics and Reynolds effect have been assessed.Results comparison shows that slop of lift curve(C_(Lα))varies very little and drag coefficient(C_D)is of a difference of 0.0004 around the design point with Ma=0.78 and lift coefficient(C_L)=0.5.Test data indicates good agreement.Reynolds number effect on CHN-T1 calibration model aerodynamic characteristics follows the expected trends.
引文
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[3]Levy D W,Zickuhr T,Vassberg J,et al.Summary of data from the first AIAA CFD drag prediction workshop[R].AIAA-2002-0841,2002.
[4]Laflin K R,Brodersen O,Rakowitz M,et al.Summary of data from the second AIAA CFD drag prediction workshop[R].AIAA-2004-555,2004.
[5]Vassberg J C,Tinoco E N,Mani M,et al.Summary of the third AIAA CFD drag prediction workshop[R].AIAA-2007-260,2007.
[6]Vassberg J C,Tinoco E N,Mani M,et al.Summary of the fourth AIAA CFD drag prediction workshop[R].AIAA-2010-4547,2010.
[7]Levy D W,Laflin K R,Tinoco E N,et al.Summary of data from the fifth AIAA CFD drag prediction workshop[R].AIAA-2013-0046,2013.
[8]Tinoco E N,Brodersen O P,Keye S,et al.Summary of data from the sixth AIAA CFD drag prediction workshop:CRMcases 2to 5[R].AIAA-2017-1208,2017.
[9]Gatlin G M,Rivers M B,Goodliff S L,et.al.Experimental investigation of the DLR-F6 transport configuration in the national transonic facility[R].AIAA-2008-6917,2008.
[10]Rivers M B,Dittberner A,Experimental investigation of the NASA common research model[R].AIAA-2010-4218,2010.
[11]Gebbink R T,Wang G L,Zhong M.High-speed wind tunnel test of the CAE-AVM for CFD validation purposed[R].AIAA-2017-0332,2017.
[12]Rivers M B,Dittberner A.Experimental investigations of the NASA common research model in the NASA Langley National Transonic Facility and NASA Ames 11-Ft transonic wind tunnel[R].AIAA-2011-1126,2011.
[13]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.
[14]范利涛,张晖,高大鹏,等.8米×6米风洞大展弦比运输机标模体系建设进展[C].第四届近代实验空气动力学会议论文集.2014.Fan L T,Zhang H,Gao D P,et al.8m×6m wind tunnel large aspect ratio calibration model system development[C].Proc of the Fourth Modern Experimental Aerodynamics Conference.2014.
[15]Fan L T,Duan X F,Xue W.Advances in test techniques based on multifunctional sting support system for 8m×6m wind tunnel[J].Applied Mechanics and Materials,2013,(336-338):880-884.
[16]Philipsen I,Hegen S,Hoeijmakers H.Advances in propeller simulation testing at the german-dutch wind tunnels(DNW)[R].AIAA-2004-2502,2004.
[17]Eckert D.Correction of support influences on measurements with sting mounted wind tunnel models[C]//Proc of the AGARD Meeting on Wall Interference,Support Interference and Flow Field Measurements.1993.