Study on the support interference of vane suspension support system in high speed wind tunnels

Li Qiang; Liu Dawei; Chen Dehua

doi:10.11729/syltlx20160053

Volume 31 Issue 1

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Li Qiang, Liu Dawei, Chen Dehua. Study on the support interference of vane suspension support system in high speed wind tunnels[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(1): 100-108. doi: 10.11729/syltlx20160053

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Study on the support interference of vane suspension support system in high speed wind tunnels

doi: 10.11729/syltlx20160053

Li Qiang^{1, 2
,
,},
Liu Dawei^{1, 2},
Chen Dehua^{1, 2}

1.
State Key Laboaratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
2.
High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2016-03-26
Rev Recd Date: 2016-06-18
Publish Date: 2017-02-25

Abstract

Abstract

Experiments with and without fake vanes are conducted using Ty-154 standard model, and the interference magnitudes are acquired. Chimera grids are used in numerical investigation. Through the work of experiments and CFD, the interference mechanisms are studied, the influence of model's breakage caused by the vanes is investigated, and the sting and belly blade support methods are also brought to compare with the vanes. The numerical results coincide well with experiments, proving the reliability of the study method. Due to the vanes' interference, the C_D increase about 0.0005 and a small head-up pitching moment occurs while C_L changes little. The vane support shows apparent advantages over sting and belly blade support in support interference characteristics. Under the Ma>0.9 condition, the vanes' interference increases and becomes unpredictable. The influence of the crack between the front vane and the fuselage as well as the shaft of back vane is small.
- vane suspension support,
- support interference,
- wind tunnel test,
- CFD,
- chimera grids

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References(17)

References

[1]	陈德华, 林俊, 郭旦平, 等. 大型飞机高速气动力关键问题解决的技术手段及途径[J]. 流体力学实验与测量, 2004, 18 (2): 1-5. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200402001.htm Chen D H, Lin J, Guo D P, et al. Technical ways to solve high speed key aerodynamic problems of large air transporters[J]. Experments and Measurements in Fluid Mechanics, 2004, 18 (2): 1-5. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200402001.htm
[2]	程厚梅. 风洞实验干扰及修正[M]. 北京: 国防工业出版社, 2003.
[3]	熊能, 林俊, 贺中, 等. 大飞机布局模型跨声速风洞实验尾支撑干扰研究[J]. 实验流体力学, 2012, 26 (2): 51-55. http://www.syltlx.com/CN/abstract/abstract10559.shtml Xiong N, Lin J, He Z, et al. Study on the rear sting support interference for large transports configuration model in transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2012, 26 (2): 51-55. http://www.syltlx.com/CN/abstract/abstract10559.shtml
[4]	祝明红, 孙海生, 金玲, 等. 低速大迎角张线尾撑系统支架干扰影响研究[J]. 实验流体力学, 2011, 25 (3): 1-3. http://www.syltlx.com/CN/abstract/abstract10647.shtml Zhu M H, Sun H S, Jin L, et al. Study on the support interference of wire-assistant sting support at high angle of attack in low speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2011, 25 (3): 1-3. http://www.syltlx.com/CN/abstract/abstract10647.shtml
[5]	沈礼敏, 沈志宏, 黄勇, 等. 低速风洞大攻角张线式支撑系统[J]. 流体力学实验与测量, 1998, 12 (4): 15-21. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC804.002.htm Shen L M, Shen Z H, Huang Y, et al. A wire type-support system for high angle of attack test in low speed wind tunnel[J]. Experiments and Measurements in FLuid Mechanics, 1998, 12 (4): 15-21. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC804.002.htm
[6]	赵子杰, 高超, 张正科, 等. 新型人工转捩技术及风洞试验验证[J]. 航空学报, 2015, 36 (6):1830-1838. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201506011.htm Zhao Z J, Gao C, Zhang Z K, et al. An innovative artificial transition technique and its validation through wind tunnel tests[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36 (6):1830-1838. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201506011.htm
[7]	王发祥. 高速风洞试验[M]. 北京: 国防工业出版社, 2003.
[8]	段卓毅, 王运涛, 庞宇飞, 等. 无尾布局干扰数值模拟[J]. 实验流体力学, 2007, 21 (4): 13-17. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200704003.htm Duan Z Y, Wang Y T, Pang Y F, et al. Numerical simulation of support interference on a tailless configuration[J]. Journal of Experiments in Fluid Mechanics, 2007, 21 (4): 13-17. http://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200704003.htm
[9]	李孝伟, 范绪箕, 乔志德. 嵌套网格技术中的Collar网格和虚拟网格方法[J]. 计算物理, 2003, 20 (2): 111-118. http://www.cnki.com.cn/Article/CJFDTOTAL-JSWL200302004.htm Li X W, Fan X Q, Qiao Z D. Collar grid and virtual grid methods in embedding technique[J]. Chinese Journal of Computional Physics, 2003, 20 (2): 111-118. http://www.cnki.com.cn/Article/CJFDTOTAL-JSWL200302004.htm
[10]	Stan A G, Richard S C. Vane support system (VSS) a new generation wind tunnel model support system[C]. 29th Aerospace Sciences Meeting, 1991.
[11]	Aavin P V. Report of investigations experimental of CT-26-1 calibration model at TsAGI T-106 wind tunnel[R]. TsAGI, 2008.
[12]	Masataka K. Wall and support interference corrections of NASA common research model wind tunnel tests in JAXA[R]. AIAA-2013-0963, 2013.
[13]	阎超. 计算流体力学方法及应用[M]. 北京: 北京航空航天大学出版社, 2006.
[14]	章荣平, 王勋年, 李真旭, 等. 低速风洞尾撑支杆干扰研究[J]. 实验流体力学, 2006, 20 (3): 22-38. http://www.syltlx.com/CN/abstract/abstract9494.shtml Zhang R P, Wang X N, Li Z X, et al. Investigation of sting support interference in low speed wind tunnel[J]. Journal of Experiments in FLuid Mechanics, 2006, 20 (3): 22-38. http://www.syltlx.com/CN/abstract/abstract9494.shtml
[15]	Lars E E. Viscousinteration or support interference-the dynamicist's dilemma[J]. AIAA Journal, 1978, 16 (4): 363-368. doi: 10.2514/3.60898
[16]	Lynch F T. The crucial role of wall interference, support interference, and flow field measurments in the development of advanced aircraft configurations[R]. AGARD, 1993.
[17]	Whitby D. Wind tunnel support system effects on a fighter aircraft model at Mach numbers from 0.6 to 2.0[C]. 29th Aerospace Sciences Meeting, 1991.