Design and construction progress of AVIC <i>Φ</i>1.0 m hypersonic wind tunnel

GAO Liangjie; XIN Yanan; YUAN Ye; LI Qiang; QIAN Zhansen

doi:10.11729/syltlx20210105

Volume 36 Issue 1

Mar. 2022

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Journal of Experiments in Fluid Mechanics > 2022 > 36(1): 44-51. > DOI: 10.11729/syltlx20210105

GAO L J，XIN Y N，YUAN Y，et al. Design and construction progress of AVIC Φ1.0 m hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022，36（1）：44-51.. DOI: 10.11729/syltlx20210105

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Design and construction progress of AVIC Φ1.0 m hypersonic wind tunnel

GAO Liangjie^{1, 2, 3,},
XIN Yanan^{1, 2, 3},
YUAN Ye^{1, 2},
LI Qiang^{1, 2},
QIAN Zhansen^{1, 2, 3, ,}

1.
AVIC Aerodynamics Research Institute, Shenyang　110034, China
2.
Key Laboratory of Hypersonic Aerodynamic Force and Heat Technology, Shenyang　110034, China
3.
Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Force Research, Shenyang　110034, China

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Received Date: August 23, 2021
Revised Date: September 29, 2021
Accepted Date: October 18, 2021

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Abstract

Abstract

The 1 m hypersonic wind tunnel for the AVIC （FL-64） is the newly built blow down free jet type large-diameter conventional hypersonic wind tunnel in China. It adopts the blowing type operation mode, at the same time, considering the test requirements of low dynamic pressure, a vacuum exhaust system is also equipped. The overall performance, key component design, flow field calibration and preliminary standard model test results of the FL-64 wind tunnel are presented in detail. The performance of the wind tunnel are as follows: the range of Mach number: 4.0 – 8.0; the total pressure range of the settling chamber: 0.1 – 8.0 MPa; the total temperature range of the settling chamber: 300 – 900 K; the unit Reynolds number range: 3.3×10⁶ – 4.6×10⁷ m^–1; the effective operating time is not less than 30 s. The FL-64 wind tunnel combined the FL-60 trisonic （Subsonic, Transonic, Supersonic） wind tunnel forming the high and low Mach number range, this can cover the wide-speed range aircraft test with a Mach number of 0.3 – 8.0. Especially the duplication capability of the total enthalpy of Mach number 4.0 can match the real flight conditions. Overall, the successful completion of the FL-64 wind tunnel provide an effective test platform for the development of nation’s high Mach number aircraft.
- hypersonic,
- large-scale wind tunnel,
- aerodynamic test,
- wind tunnel design,
- flow field calibration

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[1]	GRAY J D, LINDSAY E. Force tests of standard hypervelo-city ballistic models HB-l and HB-2 at Mach 1.5 to 10[R]. AEDC-TDR-64-137, 1964.
[2]	VANDERCREEK C, SMITH M, YU K. Focused schlieren and deflectometry at AEDC hypervelocity wind tunnel no.9 [R]. AIAA-2010-4209, 2010. doi: 10.2514/6.2010-4209
[3]	KUCHI-ISHI S, WATANABE S, NAGAI S, et al. Compara-tive force/heat flux measurements between JAXA hypersonic test facilities using standard model HB-2(part 1: 1.27 m hyper-sonic wind tunnel results)[R]. JAXA-RR-04-035E, 2005.
[4]	许晓斌. 常规高超声速风洞与试验技术[M]. 北京: 国防工业出版社, 2005.
[5]	孙勇堂,赵之平,石运军,等. CAAA新建Φ1.2米常规高超声速风洞[C]//中国力学大会−2017暨庆祝中国力学学会成立60周年大会论文集. 2017.
[6]	徐翔,程克明,王志坚,等. 南航Φ0.5 m高超声速风洞流场校测[J]. 实验流体力学,2009,23(4):77-81. DOI: 10.3969/j.issn.1672-9897.2009.04.016 XU X,CHENG K M,WANG Z J,et al. Flow field calibration of NUAA Φ0.5 m hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2009,23(4):77-81. doi: 10.3969/j.issn.1672-9897.2009.04.016
[7]	刘中臣,钱战森,冷岩,等. 声爆近场空间压力风洞测量技术[J]. 航空学报,2020,41(4):123596. DOI: 10.7527/S1000-6893.2019.23596 LIU Z C,QIAN Z S,LENG Y,et al. Wind tunnel measure-ment techniques for sonic boom near-field pressure[J]. Acta Aeronautica et Astronautica Sinica,2020,41(4):123596. doi: 10.7527/S1000-6893.2019.23596
[8]	高亮杰,钱战森,王璐,等. 高马赫数低噪声风洞层流喷管设计与性能评估[J]. 航空科学技术,2016,27(8):68-78. GAO L J,QIAN Z S,WANG L,et al. Design and performan-ce evaluation for high Mach number low noise wind tunnel nozzle[J]. Aeronautical Science & Technology,2016,27(8):68-78.

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