高焓激波风洞试验技术综述
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摘要
高焓激波风洞是研究高温真实气体效应主要的地面模拟设备,基于高焓激波风洞发展的试验技术主要包括驱动技术、流场检测技术和测试技术。决定试验段所能达到的总焓和总压水平的驱动技术,主要包括变截面驱动、多段驱动、轻质气体驱动和加热轻质气体驱动;高焓激波风洞驻室温度高,导致激波管末端和喉道等内流道产生烧蚀并对流场带来污染,并且在高温条件下气体分子发生离解甚至电离,导致试验分析困难;确定试验段自由来流参数和有效时间以及污染气体推迟的流场检测技术,是开展风洞试验的前提条件;高焓激波风洞总焓和总压高,有效试验时间毫秒量级,对测试技术提出了更高的要求。本文综述相关技术的研究进展,重点介绍了气动热/气动力以及流场物理化学参数的测试技术,指出进一步的技术发展方向,以期为大型高焓激波风洞的发展与应用提供参考。
High enthalpy shock tunnel is the main ground testing equipment for the study of high enthalpy flows.The experimental technology of high enthalpy shock tunnel mainly includes the driver technology,the detection technology,and the testing technology.The driver methods determine the achievable total enthalpy and pressure level in the test section.These methods contain variable cross section driver,multicascade compression driver,light gases driver,and heated light gases driver.The extremely high temperature is produced in the high enthalpy shock tunnel.The high temperature leads to the melting effects at the end of shock tube and nozzle throat,resulting in the driver gas contamination in the flow field.It is difficult to analyze the test results due to the component dissociation and the frozen vibration temperature.The free stream condition,the duration of the working time,and the delay technology of driver gas contamination are confirmed by the detection technology,which plays the primary role in high enthalpy shock tunnel.There are not only high total temperature and pressure in high enthalpy shock tunnel,but also the duration of the working time is only several milliseconds,which bring more level high standard of the testing technique is required for high enthalpy shock tunnel in consideration of high total temperature,high pressure,and the only several milliseconds duration of the working time.The research progress of the related technology is introduced,and an emphasized introduction is given for the testing technology of aerodynamic force/heat and the flow field physical-chemical parameters.The direction of the further technological development is pointed out,which can provide references for the development and application of large-scale high enthalpy shock tunnel.
High enthalpy shock tunnel is the main ground testing equipment for the study of high enthalpy flows.The experimental technology of high enthalpy shock tunnel mainly includes the driver technology,the detection technology,and the testing technology.The driver methods determine the achievable total enthalpy and pressure level in the test section.These methods contain variable cross section driver,multicascade compression driver,light gases driver,and heated light gases driver.The extremely high temperature is produced in the high enthalpy shock tunnel.The high temperature leads to the melting effects at the end of shock tube and nozzle throat,resulting in the driver gas contamination in the flow field.It is difficult to analyze the test results due to the component dissociation and the frozen vibration temperature.The free stream condition,the duration of the working time,and the delay technology of driver gas contamination are confirmed by the detection technology,which plays the primary role in high enthalpy shock tunnel.There are not only high total temperature and pressure in high enthalpy shock tunnel,but also the duration of the working time is only several milliseconds,which bring more level high standard of the testing technique is required for high enthalpy shock tunnel in consideration of high total temperature,high pressure,and the only several milliseconds duration of the working time.The research progress of the related technology is introduced,and an emphasized introduction is given for the testing technology of aerodynamic force/heat and the flow field physical-chemical parameters.The direction of the further technological development is pointed out,which can provide references for the development and application of large-scale high enthalpy shock tunnel.
引文
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[23]Itoh K,Takahashi M,Komuro T.Effectod throat melting on nozzle flow characteristic in high enthalpy shock tunnel[C]//Proceedings of the 22nd International Symposium on Shock Waves,1999:459-464.
[24]Yu Hongru.Oxy-hydrogen combustion and detonation driven shock tube[J].Acta Mechanica Sinica,1999,631(4):389-396.(in Chinese)俞鸿儒.氢氧燃烧及爆轰驱动激波管[J].力学学报,1999,31(4):389-396.
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[27] Michael S Holden,Timothy P Wadhams,Matthew MacLean,et al.Experimental studies in LENS I and X to evaluate real gas effects on hypervelocity vehicle performance[R].AIAA 2007-204.
[28] Holden M.Large energy national shock tunnel(LENS).description and capabilities brochure[R].Calspan-UB Research Center,1991.
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[31]Stalker R J,Crane K C.Driver gas contamination in a highenthalpy reflected shock tunnel[J].AIAA Journal,1978,16(3):277-279.
[32]Sudani N.Gasdynamical detectors of driver gas contamination in a high-enthalpy shock tunnel[J].AIAA Journal,1998,36(3):313-320.
[33]Suani N,Hornung H.Detection and reduction of driver gas contamination inahigh-enthalpyshock-tunnel[C]//Proceedings 21st International Symposiums on Shock Waves.P543-548,Great Kppel Island.Australia.
[34]Frank K Lu,Dan E M.Advanced hypersonic test facilities[M].ISBN 978-7-5165-0955-5.
[35]Grossir G,Paris S,Rambaud P.Design of static pressure probes for improved free-steam characterization in hypersonic wind tunnels[R].AIAA 2014-1410.
[36]Grossir G,Rambaud P.Detection of nitrogen flow condensation in a hypersonic wind tunnel using a static pressure probe[R].AIAA 2014-1153.
[37] Wehe S D, Baer D S.Tunable diode laser absorption measurementsoftemperature, velocityandH2Oin hypervelocity flows[R].AIAA-97-3267,1997.
[38] Mirels H.Shock tube test time limitation due to turbulent-wall boundary layer[J].AIAA Journal,1964,2:38-54.
[39]Sudani N. Test time increase by delaying driver gas contamination for reflected shock tunnels[R].AIAA-98-2771,1998.
[40] Hannemann K,Schnieder M,Reimann B.The influence and the delay of driver gas contamination in HEG[R].AIAA 2000-2593.
[41]Olivier H,Vetter M,Jessen C.Measurements on models for hypersonic real gas conditions[R]. New Trends in Instrumentation for Hypersonic Research[M].Boutier A Ed.Kluwer,Dordrecht,Netherland,1993.
[42] Holden M S, Wadhams T P,Candler G V.Experimental studies in the LENS shock and expansion tunnels to examine real-gas effects in hypersonic flows[R].AIAA 2004-0916.
[43] Holden M S,Wadhams T P.Code validation study of laminar shock/boundarylayerandshock/shockinteractionsin hypersonic flow.Part A:Experimental Measurements[R].AIAA 2001-1031.
[44] Hubner J,Carroll B,Schanze J H.Temperature and pressure sensitive paint measurements in short duration hypersonic flow[R].AIAA-99-0388,1999.
[45] Holden M S.The LENS facilities and experimental studies to evaluate the modeling of boundary layer transition,shock/boundary layer interaction,real gas,radiation and plasma.phenomena in contemporary CFD codes[R].RTO-EN-AVT-186.
[46]Bi Z X,Han S G,Wu C H,et al.Phosphor thermography study in gun tunnel[J].Journal of Experiments in Fluid Mechanics,2013,27(3):87-92.(In Chinese)毕志献,韩曙光,伍超华,等.磷光热图测热技术研究[J].实验流体力学,2013,27(3):87-92.
[47]Lin Z B,Guo D H,Zhu N Y.The measurement and diagnostics in free stream of JF-10 hydrogen oxygen detonation driven shock tunnel[J].Experiments and Measurements in Fluid Mechanics,2000,14(3):12-17.(in Chinese)林贞彬,郭大华,竺乃宜.JF-10氢氧爆轰驱动激波风洞自由流的测量和诊断[J].流体力学实验与测量,2000,14(3):12-17.
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