General performance of 0.6m continuous transonic wind tunnel

Liao Daxiong; Chen Jiming; Zheng Juan; Chen Qin; Pei Haitao; Wu Shenghao

doi:10.11729/syltlx20170086

Volume 32 Issue 6

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2018 > 32(6): 88-93

Liao Daxiong, Chen Jiming, Zheng Juan, et al. General performance of 0.6m continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(6): 88-93. doi: 10.11729/syltlx20170086

Citation:

PDF( 4086 KB)

General performance of 0.6m continuous transonic wind tunnel

doi: 10.11729/syltlx20170086

Liao Daxiong^{1, 2
,},
Chen Jiming^{1, 2
,
,},
Zheng Juan¹,
Chen Qin^{1, 2},
Pei Haitao²,
Wu Shenghao²

1.
State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
2.
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2017-06-28
Rev Recd Date: 2018-10-15
Publish Date: 2018-12-25

Abstract

Abstract

The 0.6m continuous transonic wind tunnel of CARDC, a circling wind tunnel, use dry air in variable density as working medium. The major components of the wind tunnel include broad-performance compressor, semi-flexible nozzle, lower-noise test section, re-entry flaps and slots, heat-exchange system and the second throat with wall flaps and center body. In order to get the general performance and the secure running boundary of the wind tunnel, the general performance calibration is carried out. Calibration results indicate that the general performances and each section of the wind tunnel agree well with the requirements. The compressor, heat-exchange system and other auxiliary equipments are all in working order. The range of total pressure in settling chamber is 15~250kPa and the control precision of the total pressure is better than 0.2%. The Mach number in the test section is in the range of 0.144~1.640 and the control precision of the Mach number is better than 0.002. The flow qualities such as the fluctuation of Mach number distribution have met the requirements(Ma ≤ 1.0, σ_Ma < 0.002;1.0 < Ma ≤ 1.6, σ_Ma < 0.008). When the Mach number is greater than 0.5, the flow fluctuation coefficient which is used to represent the noise level is below 0.8%. The design scheme's feasibility of the 0.6m continuous transonic wind tunnel is fully verified by the debugging results, which provide scientific guidance for the development of the large-scale continuous transonic wind tunnel.
- continuous transonic wind tunnel,
- general performance,
- slotted test section,
- flow-field quality,
- wind tunnel calibration

FullText(HTML)

References(14)

References

[1]	Barnwell R W, Edwards C L W, Kolgore R A, et al. Optimum transonic wind tunnel[C]//Proc of the 14th Aerodynamic Testing Conference.1986.
[2]	廖达雄, 陈吉明, 彭强, 等.连续式跨声速风洞设计关键技术[J].实验流体力学, 2011, 25(4):74-78. doi: 10.3969/j.issn.1672-9897.2011.04.014 Liao D X, Chen J M, Peng Q, et al. Key design techniques of the low noise continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(4):74-78. doi: 10.3969/j.issn.1672-9897.2011.04.014
[3]	Mabey D G. Some remarks on the design of transonic tunnels with low levels of flow unsteadiness[R]. NASA-CR-2722, 1976.
[4]	李峰, 高超, 张正科, 等. NF-6增压连续式跨声速风洞流场特性与标模试验[J].实验流体力学, 2013, 27(1):61-64. doi: 10.3969/j.issn.1672-9897.2013.01.011 Li F, Gao C, Zhang Z K, et al. The test of characteristics of flow area and calibration model in NF-6 pressurized continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(1):61-64. doi: 10.3969/j.issn.1672-9897.2013.01.011
[5]	周廷波, 高超, 张正科, 等. NF-6喷液氮降温系统研制[J].航空动力学报, 2018, 33(2):327-337. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201802010 Zhou T B, Gao C, Zhang Z K, et al. Development of liquid nitrogen injection cooling system of NF-6 wind tunnel[J]. Journal of Aerospace Power, 2018, 33(2):327-337. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201802010
[6]	波普, 戈因.高速风洞试验[M].北京:科学出版社, 1980. Pope A, Goin K L. High-speed wind tunnel testing[M]. Beijing:Science Press, 1980.
[7]	Wolf T. State of the art in circuit loss analysis of transonic wind tunnels[C]//Proc of the 20th AIAA Advanced Measurement and Ground Testing Technology Conference, 1998.
[8]	国防科学技术工业委员会.高速风洞和低速风洞流场品质规范: GJB 1179-91[S].北京: 国防科工委军标出版社, 1992.
[9]	恽起麟.实验空气动力学[M].北京:国防工业出版社, 1997.
[10]	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.
[11]	熊波, 周恩民, 程松, 等. 0.6m连续式风洞调试运行关键技术研究[J].实验流体力学, 2016, 30(4):81-86. http://www.syltlx.com/CN/abstract/abstract10956.shtml Xiong B, Zhou E M, Cheng S, et al. Research on key technologies of debugging and operating in 0.6m×0.6m continuous transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(4):81-86. http://www.syltlx.com/CN/abstract/abstract10956.shtml
[12]	熊波, 程松, 罗新福, 等.低雷诺数效应对0.6m连续式风洞性能影响[J].实验流体力学, 2017, 31(1):87-92. http://www.syltlx.com/CN/abstract/abstract11001.shtml Xiong B, Cheng S, Luo X F, et al. Effects of low Reynolds number on performance of 0.6m continuous wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(1):87-92. http://www.syltlx.com/CN/abstract/abstract11001.shtml
[13]	丛成华, 廖达雄, 陈吉明, 等.跨声速风洞第二喉道性能计算[J].航空动力学报, 2010, 25(9):2050-2056. doi: 10.3109-09513590903215458/ Cong C H, Liao D X, Chen J M, et al. Numerical investigation on performance of second throat in transonic wind tunnel[J]. Journal of Aerospace Power, 2010, 25(9):2050-2056. doi: 10.3109-09513590903215458/
[14]	赵波, 廖达雄, 陈吉明, 等.连续式跨超声速风洞热交换器设计技术初步研究[J].空气动力学学报, 2010, 28(06):696-702. doi: 10.3969/j.issn.0258-1825.2010.06.014 Zhao B, Liao D X, Chen J M, et al. Investigation of heat exchanger design for continuous transonic and supersonic wind tunnel[J]. Acta Aerodynamica Sinica, 2010, 28(06):696-702. doi: 10.3969/j.issn.0258-1825.2010.06.014