ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Effective test time measurement research for high enthalpy shock tunnel
Received date: 2014-12-03
Revised date: 2015-01-08
Online published: 2015-01-12
Supported by
National Natural Science Foundation of China (11402275)
The high enthalpy shock tunnel, which can provide the high-temperature gas conditions for hypersonic flight, is an effective ground facility for the research of reentry problems. It also has the ability of studying real gas effect. However, the effective test time of a high enthalpy shock tunnel is short, in the order of milliseconds, and the higher of the enthalpy value, the shorter the test time. In such a short time, determination of the effective test time from the test curve for a high enthalpy shock tunnel is highly important, or the reliability and accuracy of the experimental result will be affected. This paper is based on the JF-10 high enthalpy shock tunnel in the Institute of Mechanics. The hypersonic test flow condition with the stagnation enthalpy of 16 MJ/kg and stagnation temperature of 7700 K is achieved using the forward detonation method. The experiments of pressure measurement, electrostatic probe, non-contact optical measurement and heat flux measurement are conducted. The nozzle starting time and effective test time are then studied. Results show that under the above test condition, the nozzle starting time of the JF-10 high enthalpy shock tunnel is about 1.3 ms and effective test time is about 2 ms. And electrostatic probe method turns out to be the most effective for determining the nozzle starting time, effective test time and arrival of the driving gas.
WANG Qiu , ZHAO Wei , YU Xilong , JIANG Zonglin . Effective test time measurement research for high enthalpy shock tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015 , 36(11) : 3534 -3539 . DOI: 10.7527/S1000-6893.2015.0014
[1] Bertin J J, Cummings R M. Critical hypersonic aerothermodynamic phenomena[J]. Annual Review of Fluid Mechanics, 2006, 38:129-157.
[2] Yu Z B, Liu Z C, Chen Z H, et al. Structure design and research of 2 m supersonic wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(2):197-207(in Chinese).虞择斌,刘政崇,陈振华,等. 2 m超声速风洞结构设计与研究[J].航空学报, 2013, 34(2):197-207.
[3] Yu H R, Zhao W, Yuan S X. Shock tunnel with H2-O2 detonation driver[J]. Aerodynamic Experiment and Measurement & Control, 1993, 7(3):38-42(in Chinese).俞鸿儒,赵伟,袁生学.氢氧爆轰驱动激波风洞的性能[J].气动实验与测量控制, 1993, 7(3):38-42.
[4] Boyce R R, Takahashi M, Stalker R J. Mass spectrometric measurements of driver gas arrival in the T4 free-piston shock-tunnel[J]. Shock Waves, 2005, 14(5/6):371-378.
[5] Petersen E L, Hanson R K. Nonideal effects behind reflected shock waves in a high-pressure shock tube[J]. Shock Waves, 2001, 10(6):405-420.
[6] Li J P, Feng H, Jiang Z L. Gas contamination induced by the interaction of shock/boundary layer in shock tunnel[J].Chinese Journal of Theoretical and Applied Mechanics, 2008, 40(3):289-296(in Chinese).李进平,冯珩,姜宗林.激波/边界层相互作用诱导的激波风洞气体污染问题[J].力学学报, 2008, 40(3):289-296.
[7] Hannemann K, Schnieder M, Reimann B, et al. The influence and the delay of driver gas contamination in HEG, AIAA-2000-2593[R]. Reston:AIAA, 2000.
[8] Paull A, King M D. A driver gas detection device for shock tunnels[J]. Shock Waves, 1995, 4(5):289-291.
[9] Sudani N, Hornung H G. Gasdynamical detectors of driver gas contamination in a high enthalpy shock tunnel[J]. AIAA Journal, 1998, 36(3):313-319.
[10] Chue R S M, Tsai C Y, Bakos R J. Driver gas contamination in a detonation driven reflected shock tunnel[J]. Shock Waves, 2004, 13(5):367-380.
[11] Yu H R, Esser B, Lenartz M, et al. Gaseous detonation driver for a shock tunnel[J]. Shock Waves, 1992, 2(4):245-254.
[12] Jiang Z L, Yu H R. Progress of the research on hypersonic shock tunnels[J]. Advances in Mechanics, 2009, 39(6):766-776(in Chinese).姜宗林,俞鸿儒.高超声速激波风洞研究进展[J].力学进展, 2009, 39(6):766-776.
[13] Yu H R. Oxyhydrogen combustion and detonation driven shock tube[J]. Acta Mechanica Sinaca, 1999, 15(2):97-107.
[14] Jiang Z L, Zhao W, Wang C. Forward-running detonation drivers for high-enthalpy shock tunnels[J]. AIAA Journal, 2002, 40(10):2009-2016.
[15] Zhao W, Jiang Z L, Saito T, et al. Performance of a detonation driven shock tunnel[J]. Shock Waves, 2005, 14(1-2):53-59.
[16] Li J P. Investigation into essential problems of detonation-driven high enthalpy shock tunnels[D]. Beijing:Institute of Mechanics, Chinese Academy of Sciences, 2007(in Chinese).李进平.爆轰驱动高焓激波风洞关键问题研究[D].北京:中国科学院力学研究所, 2007.
[17] Wang Q. Experimental study on characteristics of heat transfer and electron density in high enthalpy flow[D]. Beijing:Institute of Mechanics, Chinese Academy of Sciences, 2013(in Chinese).汪球.高焓流动气动热和电子密度特性实验研究[D].北京:中国科学院力学研究所, 2013.
[18] Le J L, Zhang R L, Wang S, et al. Research of non-equilibrium structure of strong shock front[J]. Journal of Experiments in Fluid Mechanics, 2006, 20(2):36-39(in Chinese).乐嘉陵,张若凌,王苏,等.强激波阵面的非平衡结构研究[J].实验流体力学, 2006, 20(2):36-39.
[19] Zeng H, Yu X L, Li F, et al. Nitric oxide concentration and temperature measurement for shockwave tunnel free stream using mid-infrared absorption spectroscopy[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(2):79-83(in Chinese).曾徽,余西龙,李飞,等.中红外吸收光谱测量激波风洞自由流中NO浓度和温度[J].实验流体力学, 2015, 29(2):79-83.
[20] Meng S H, Ding X H, Yi F J, et al. Overview of heat measurement technology for hypersonic vehicle surfaces[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(7):1759-1775(in Chinese).孟松鹤,丁小恒,易法军,等.高超声速飞行器表面测热技术综述[J].航空学报, 2014, 35(7):1759-1775.
/
| 〈 |
|
〉 |
CJA