Experimental research of special perforated wall test section for transonic wind tunnel

LIU Qin; ZHANG Guobiao; ZHANG Zhifeng; ZHANG Cheng

doi:10.11729/syltlx20190073

Volume 34 Issue 5

Oct. 2020

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LIU Qin, ZHANG Guobiao, ZHANG Zhifeng, et al. Experimental research of special perforated wall test section for transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(5): 103-108. doi: 10.11729/syltlx20190073

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Experimental research of special perforated wall test section for transonic wind tunnel

doi: 10.11729/syltlx20190073

Facility Design and Instrumentation Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2019-05-20
Rev Recd Date: 2019-06-27
Publish Date: 2020-10-25

Abstract

Abstract

The perforated test section of the 2.4 m×2.4 m injection driven transonic wind tunnel is redesigned so as to study the aerodynamic force of advanced aircraft. A scaled experimental research of the special perforated wall test section is conducted in the 0.24 m×0.20 m transonic wind tunnel (the pilot wind tunnel of the 2.4 m×2.4 m transonic wind tunnel). The experimental study has demonstrated that the project is feasible, and the flow quality of the flow field in the special perforated wall test section reaches the required specification. Influences of the diffuse angle in the test section, the open width of the mainstream ejected slot and the porosity of the perforated wall are also investigated. The results have been used to design the perforated test section of the 2.4 m×2.4 m transonic wind tunnel. The calibration parameters for the future perforated test section flow field calibration in this tunnel are also provided.
- transonic wind tunnel,
- test section,
- perforated,
- experimental research,
- aerodynamics design

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References(15)

References

[1]	丛成华, 刘琴, 张志峰, 等.专用跨声速风洞开孔壁试验段设计数值模拟[J].航空学报, 2012, 33(6):1014-1019. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201206006 CONG C H, LIU Q, ZHANG Z F, et al. Numerical simulation of design of transonic wind tunnel perforated test section[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(6):1014-1019. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201206006
[2]	刘琴, 陈志强, 申江, 等.利用M1.4喷管和开孔壁试验段实现低超声速流场实验研究[J].实验流体力学, 2011, 25(1):84-87. http://www.syltlx.com/CN/abstract/abstract10703.shtml LIU Q, CHEN Z Q, SHEN J, et al. Experimental research of low supersonic flow field for M1.4 nozzle and perforated wall test section[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(1):84-87. http://www.syltlx.com/CN/abstract/abstract10703.shtml
[3]	LAWSON S J, BARAKOS G N. Review of numerical simulations for high-speed, turbulent cavity flows[J]. Progress in Aerospace Sciences, 2011, 47(3):186-216. doi: 10.1016/j.paerosci.2010.11.002
[4]	刘政崇, 廖达雄, 董谊信, 等.高低速风洞气动与结构设计[M].北京:国防工业出版社, 2003. LIU Z C, LIAO D X, DONG Y X, et al. Aerodynamic design and structure design of wind tunnel[M]. Beijing:National Defense Industry Press, 2003.
[5]	REED T D, POPE T C, COOKSEY J M. Calibration of transonic and supersonic wind tunnels[R]. NASA-CR-2920, 1977.
[6]	郑国锋.跨音速风洞实验段中气流的加速问题[J].航空学报, 1989, 10(2):B073-B075. ZHENG G F. On the accelerating airflow problem in the test section of a transonic wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 1989, 10(2):B073-B075.
[7]	MARINO A, IMPERATORE B, RAGNI A. Streamwise porosity distribution optimization for minimising wall interference in a transonic wind tunnel[R]. AIAA-2009-1485, 2009.
[8]	ELFSTROM G M, MEDVED B, RAINBIRD W J. Optimum poro-sity for an inclined-hole transonic test section wall treated for edgetone noise reduction[R]. AIAA-1988-2003, 1988.
[9]	CHAN Y Y. Analysis of boundary layers on perforated walls of transonic wind tunnels[J]. Journal of Aircraft, 1981, 18(6):469-473. doi: 10.2514/3.44716
[10]	刘光远, 王瑞波, 郭秋亭, 等. 2.4 m跨声速风洞壁板参数对核心流均匀性的影响[J].航空学报, 2015, 36(9):2930-2938. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201509014 LIU G Y, WANG R B, GUO Q T, et al. Wall parameters influence on centerline flow uniformity in 2.4 m transonic wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(9):2930-2938. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201509014
[11]	陈德华, 王维新, 王晋军, 等. 2.4 m跨声速风洞流场性能调试研究[J].空气动力学学报, 2004, 22(3):279-282. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kqdlxxb200403007 CHEN D H, WANG W X, WANG JJ, et al. Investigation on flow-field debugging for 2.4 m transonic wind tunnel[J]. Acta Aerodynamica Sinica, 2004, 22(3):279-282. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kqdlxxb200403007
[12]	恽起麟.实验空气动力学[M].北京:国防工业出版社, 1991. YUN Q L. Experimental aerodynamic[M].Beijing:National Defense Industry Press, 1991.
[13]	王发祥.高速风洞试验[M].北京:国防工业出版社, 2003. WANG F X. High-speed wind tunnel testing[M].Beijing:National Defense Industrial Press, 2003.
[14]	波普, 戈因.高速风洞试验[M].邓振瀛, 李廷林, 译.北京: 科学出版社, 1980. POPE A, GOIN K L.High-speed wind tunnel testing[M]. DENG Z Y, LI T L, translated. Beijing: Science Press, 1980.
[15]	中国人民解放军总装备部.高速风洞和低速风洞流场品质要求: GJB 1179A-2012[S].北京: 中国人民解放军总装备部军标出版社, 2012.