高超声速气动试验模拟现状与面临的新挑战
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摘要
高超声速飞行器的发展对地面试验模拟提出了新的要求,但是,现有条件还不能完全满足这些要求.文章首先回顾和概述了气动研究地面试验所应遵循的一般性相似准则,分析了现行气动力热和推进试验模拟的不足和所面临的挑战.经分析认为,面对这些挑战,现行的主要参数模拟部件相似模拟和局部相似模拟等方法仍然有效,但应加强相似理论对地面试验的指导和计算对试验的支撑性作用,并在必要时通过飞行试验对不完全相似模拟结果进行验证与确认.
New demands on ground tests were made because of the rapid development of novel hypersonic flight vehicles.However,these requirements can be hardly satisfied for the moment. In the present study,the general similarity rules of aerodynamic research in ground wind tunnels were reviewed. Then the shortcomings and challenges of ground test simulations of state-of-the-art aerodynamics,aerothermodynamics and propulsion were analyzed. It is concluded that the current critical parameter simulation,assembly simulation and local similarity simulation are still valid,whereas the ground test should be guided by similarity theory and supported by numerical calculation more intensively. Moreover,flight test should be conducted if necessary to validate and verify the results obtained with incomplete similarity simulation.
New demands on ground tests were made because of the rapid development of novel hypersonic flight vehicles.However,these requirements can be hardly satisfied for the moment. In the present study,the general similarity rules of aerodynamic research in ground wind tunnels were reviewed. Then the shortcomings and challenges of ground test simulations of state-of-the-art aerodynamics,aerothermodynamics and propulsion were analyzed. It is concluded that the current critical parameter simulation,assembly simulation and local similarity simulation are still valid,whereas the ground test should be guided by similarity theory and supported by numerical calculation more intensively. Moreover,flight test should be conducted if necessary to validate and verify the results obtained with incomplete similarity simulation.
引文
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[2]李建林.临近空间高超声速飞行器发展研究[M].北京:中国宇航出版社,2012:264-269.Li J L.Development of near space hypersonic flight vehicles[M].Beijing:China Aerospace Press,2012:264-269(in Chinese).
[3]于登云.新型航天器发展对力学学科的挑战[J].科学通报,2015,60(12):1085-1094.Yu D Y.Mechanical challenges in advanced spacecraft development[J].Chinese Science Bulletin,2015,60(12):1085-1094(in Chinese).
[4]Berry S,Daryabeigi K,Wurster K,et al.Boundary-layer transition on X-43A[J].Journal of Spacecraft and Rockets,2010,47(6):922-934.
[5]Holden M S,Wadhams T P.A review of experimental studies for DSMC and Navier-Stokes code validation in laminar regions of shock/shock and shock/boundary layer interaction including real gas effects in hypervelocity flows[R].AIAA 2003-3641,2003.
[6]Frost M A,Gangurde D Y,Paull A,et al.Boundarylayer separation due to combustion-induced pressure rise in a supersonic flow[J].AIAA Journal,2009,47(4):1050-1053.
[7]Ewing M E,Laker T S,Walker D T.Numerical modeling of ablation heat transfer[J].Journal of Thermophysics and Heat Transfer,2013,27(4):615-632.
[8]Agarwal K K,Krishna S,Ravikrishna R V.Mixing enhancement in a compact trapped vortex combustor[J].Combustion Science and Technology,2013,185(3):363-378.
[9]Gross M L,Beckstead M W,Puduppakkam K V,et al.Multi-phase combustion modeling of ammonium dinitramide using detailed chemical kinetics[R].AIAA 2006-4747,2006.
[10]Motoe M,Shimada T.Large eddy simulation of swirling combustion flow in a modeled hybrid rocket with wall fuel blowing[R].AIAA 2013-3644,2013.
[11]吴建民.高等空气动力学[M].陈则霖,吴文正,译.北京:北京航空航天大学出版社,1992:91-102.Wu J M.Advanced Aerodynamics[M].Translated by Chen Z L,Wu W Z.Beijing:Beihang University Press,1992:91-102(in Chinese).
[12]杨世铭,陶文铨.传热学[M].北京:高等教育出版社,1998:150-161.Yang S M,Tao W Q.Heat Transfer[M].Beijing:Higher Education Press,1998:150-161(in Chinese).
[13]张涵信.真实气体流动的相似规律[J].空气动力学学报,1990,8(1):1-8.Zhang H X.The similarity law for real gas flow[J].Acta Aerodynamica Sinica,1990,8(1):1-8(in Chinese).
[14]陈伟芳,石于中,曹登泰,等.流动相似律研究[J].国防科技大学学报,1999,21(4):5-8.Chen W F,Shi Y Z,Cao D T,et al.Study of flow’s similitude law[J].Journal of National University of Defense Technology,1999,21(4):5-8(in Chinese).
[15]刘磊.高超声速飞行器热气动弹性特性及相似准则研究[D].北京:中国空气动力研究与发展中心,2014.Liu L.Study on the characteristics and similarity criteria of aerothermoelasticity for hypersonic vehicles[D].Beijing:China Aerodynamics Research and Development Center Graduate School,2014(in Chinese).
[16]Romere P O,Kanipe D B,Young J C.Space shuttle entry aerodynamic comparisons of flight 1 with preflight predictions[J].Journal of Spacecraft and Rockets,1983,20(1):15-21.
[17]Holden M S,Mundy E P,Wadhams T P.A review of experimental studies of surface roughness and blowing on the heat transfer and skin friction to nosetips and slender cones in high Mach numbers flows[R].AIAA 2008-3907,2008.
[18]Bowersox R.Survey of high-speed rough wall boundary layers:invited presentation[R].AIAA 2007-3998,2007.
[19]Johnson R A,Stanek M J,Grove J E.Store separation trajectory deviations due to unsteady weapons bay aerodynamics[R].AIAA 2008-188,2008.
[20]Neville A G,Nompelis I,Subbareddy P K,et al.Effect of thermal non-equilibrium on decaying isotropic turbulence[R].AIAA 2014-3204,2014.
[21]Rini P,Thmel J,Chazot O,et al.Analysis of chemical nonequilibrium and elemental demixing within carbon dioxide plasma flows for Mars entry application[R].AIAA2007-1356,2007.
[22]Wadhams T P,Mac Lean M G,Holden M S,et al.A review of transition studies on full-scale flight vehicles at duplicated flight conditions in the LENS tunnels and comparisons with prediction methods and flight measurement[R].AIAA 2010-1246,2010.
[23]Clemente M D,Rufolo G C,Ianiro A,et al.Aerothermal coupling methodology for the rebuilding of a plasma wind tunnel test and comparison with an advanced infrared measurement technique[R].AIAA 2009-7236,2009.
[24]Gkcen T.Effects of flowfield nonequilibrium on convective heat transfer to a blunt body[J].Jounal of Thermophysics and Heat Transfer,1997,11(2):289-295.
[25]袁军娅,蔡国飙,杨红亮,等.高焓非平衡气动热环境的试验模拟及影响[J].实验流体力学,2012,26(6):35-39.Yuan J Y,Cai G B,Yang H L,et al.Test simulation of heat environment in high enthalpy nonequilibrium flow and effects[J].Journal of Experiments in Fluid Mechanics,2012,26(6):35-39(in Chinese).
[26]董维中,乐嘉陵,高铁锁.钝体标模高焓风洞试验和飞行试验相关性的数值分析[J].流体力学实验与测量,2002,16(2):1-8.Dong W Z,Le J L,Gao T S.Numerical analysis for correlation of standard model testing in high enthalpy facility and flight test[J].Experiments and Mearsurements in Fluid Mechanics,2002,16(2):1-8(in Chinese).
[27]Erickson W D.Real-gas correction factors for hypersonic flow parameters in Helium[R].NASA TN D-462,1960.
[28]郭帅帆,宋文艳,李建平,等.燃烧加热污染空气对超燃冲压发动机性能影响研究[J].推进技术,2013,34(4):493-498.Guo S F,Song W Y,Li J P,et al.Numerical investigation of effects of vitiated air on scramjet performance[J].Journal of Propulsion Technology,2013,34(4):493-498(in Chinese).
[29]Auslender A H,Suder K L,Thomas S R.An overview of the NASA FAP hypersonics project airbreathing propulsion research[R].AIAA 2009-7277,2009.
[30]邢建文,李卫强,肖保国.不同燃料燃烧加热对超燃冲压发动机性能影响的分析与评估[J].推进技术,2013,34(12):1636-1642.Xing J W,Li W Q,Xiao B G.Effects of different fueled combustion heater on scramjet performance[J].Journal of Propulsion Technology,2013,34(12):1636-1642(in Chinese).