自由射流试验中超声速进气道流场的数值研究
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摘要
应用CFD方法,通过特征线法设计超声速喷管,在喷管出口形成超声速进气道高空飞行时的工作环境。分析不同马赫数下喷管出口马赫数分布情况,发现出口核心区存在于距离喷管出口壁面垂直方向3倍边界层位移厚度的位置。简要分析了二元超声速喷管出口马赫数分布情况。将自由射流模型模拟结果与模拟飞行模型模拟结果进行比较。进气道进口斜激波分布基本一致,分布合理,与理论吻合较好,喷管的射流满足高空模拟试验要求。
Applying CFD,the supersonic nozzle w as designed in light of method of characteristics. The environment or supersonic inlet in an altitude flight w as simulatedat the outlet of that nozzle. The core area of the outlet w as found near the w all at the distance of threefold boundary layerdisplacement thickness by analyzingthe contours of M ach in different situations. A brief analysis of M ach distribution in the binary supersonic nozzle outletw as presented. The simulation results ofthe free-jet model and the flight simulation model w ere compared. There w as a consistent and reasonable distribution of oblique shock in the import of the inlet,w hich w asin good agreement w ith the theory,and therefore,fit the altitude test requirement w ell.
Applying CFD,the supersonic nozzle w as designed in light of method of characteristics. The environment or supersonic inlet in an altitude flight w as simulatedat the outlet of that nozzle. The core area of the outlet w as found near the w all at the distance of threefold boundary layerdisplacement thickness by analyzingthe contours of M ach in different situations. A brief analysis of M ach distribution in the binary supersonic nozzle outletw as presented. The simulation results ofthe free-jet model and the flight simulation model w ere compared. There w as a consistent and reasonable distribution of oblique shock in the import of the inlet,w hich w asin good agreement w ith the theory,and therefore,fit the altitude test requirement w ell.
引文
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[2]童秉纲,孔祥言,邓国华.气体动力学[M].北京:高等教育出版社,2012:139-141.
[3]王福军.计算流体动力学分析[M].北京:清华大学出版社,2004:11-119.
[4]杜鹤龄.航空发动机高空模拟[M].北京:国防工业出版社,2002:32-51.
[5]王平,段炼,马洪安.外压式超声速进气道流场的数值模拟[J].飞机设计,2009,29(5):1-3.
[6]邹宁.超声速喷管设计及其数值模拟和实验研究[D].南京:南京航空航天大学,2009.
[7]陈国飞,叶定友,刘霓生,等.超声速射流对挡流板的冲击流场的数值模拟[J].固体火箭技术.1995,(18):4.
[8]李世珍,唐硕.二维超声速进气道数值仿真研究[J].计算机仿真,2010,27(12):43.
[9]Y.Otobe,H.Kashimura,S.Mastuo,et al.Influence of nozzle geometry on the near-field structure of a highly underexpanded sonic jet[J].Journal of Fluids and Structures,24(2008):281-223.
[10]P.C.Wang,J.J.Mc Guirk.Large eddy simulation of supersonic jet plumes from rectangular con-di nozzles[J].International Journal of Heat and Fluid Flow,43(2013):1.
[11]L.Chan,C.Chin,J.Soria,et al.Large eddy simulation and Reynolds-averaged Navier-stokes calculation of supersonic imping jets at varying nozzleto-w all distances and impinging angles[J].International Journal of Heat and Fluid Flow,2014,47:31-32.
[12]P.Dubs,M.Khalij,R.Benelmir,ATazibt.Study on the dynamical characteristics of a supersonic high pressure ratio underexpanded impinging ideal gas jet through numerical simulations[J].M echanics Research Communications,38(2011):267-268.
[13]Yulia Halipovich,Benveniste Natan,Josef Rom.Numerical solution of the turbulent supersonic flow over a backw ard facing step[J].Fluid Dynamics Research,1999,24:251-252.
[14]Vincent Lijo,Heuy Dong Kim,et al.Numerical simulation of transient flow s in a rocket propulsion nozzle[J].International Journal of Heat and Fluid Flow,2010,31:209-210.
[15]伍荣林.风洞设计原理[M].北京:北京航天航空大学出版社,1985:157-170.