Correlation analysis of large low speed wind tunnel test on CHN-T1 calibration model

Zhang Hui; Fan Litao

doi:10.11729/syltlx20180046

Volume 33 Issue 3

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Article Navigation > Journal of Experiments in Fluid Mechanics > 2019 > 33(3): 106-111

Zhang Hui, Fan Litao. Correlation analysis of large low speed wind tunnel test on CHN-T1 calibration model[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(3): 106-111. doi: 10.11729/syltlx20180046

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Correlation analysis of large low speed wind tunnel test on CHN-T1 calibration model

doi: 10.11729/syltlx20180046

Zhang Hui,
Fan Litao^,

Low Speed Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2018-04-16
Rev Recd Date: 2019-01-30
Publish Date: 2019-06-25

Abstract

Abstract

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, 4.667m 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 TG1801A six-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.
- standard model,
- wind tunnel test,
- correlativity,
- test precision,
- support interference,
- balance

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References(17)

References

[1]	Belter D L, Mejia K M, Okada S D. A review of standards model testing in the Boeing transonic wind tunnel[R]. AIAA-2002-2789, 2002.
[2]	战培国, 罗月培.飞行器风洞试验标准体系研究初探[J].标准科学, 2011, 11:28-31. Zhan P G, Luo Y P. Primary research on the standard system of air vehicle calibration models used in wind tunnel test[J]. Standard Science, 2011, 11:28-31.
[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: CRM cases 2 to 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. doi: 10.7638/kqdlxxb-2018.0072 Yu Y G, Zhou Z, Huang J T, et al. Aerodynamic design of a standard model CHN-T1 for single-aisle passenger aircraft[J]. Acta Aerodynamica Sinica, 2018, 36(3):505-513. doi: 10.7638/kqdlxxb-2018.0072
[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. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=10.4028/www.scientific.net/AMM.336-338.880
[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.