6种典型飞行器的RANS计算及大分离区域的DES分析
RANS calculation and DES analysis of massively separated flows for six typical vehicles
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摘要: 提出了一种将RANS(Reynolds averaged Navier-Stokes)与DES(detached eddy simulation)相结合计算流场的工程新算法,并用于第一代载人飞船Mercury、第二代载人飞船Gemini、人类第一枚成功到达火星上空的Fire-Ⅱ探测器、具有丰富风洞实验数据(来流Mach数从0.50变到2.86)的巡航导弹、高升阻比的Waverider(乘波体)以及具有大容积效率与高升阻比的CAV(common aero vehicle)等6种国际上著名飞行器的绕流计算.在流场计算中,采用分区技术,即首先对全流场采用RANS计算,然后对分离较大或者分离较严重的那些区域采用DES分析技术.文中所完成的6个典型算例总共63个工况的数值计算表明:仅在分离较大的区域采用DES分析技术,虽然从严格意义上讲这样的处理并非真正意义上的DES,但这样近似处理后所得到的流场数值结果(其中包括气动力和气动热)与相关实验数据较为贴近,并且流场的计算效率较全场进行DES计算时要高得多.Abstract: A new method for flow field calculation in engineering combining RANS(Reynolds averaged Navier-Stokes) with DES(detached eddy simulation) was proposed,and was applied to the flow field calculation of six kinds of vehicles,such as the first generation of manned spacecraft Mercury,the second generation of manned spacecraft Gemini,the first probe of human that reached over Mars,cruise missiles that posses large quantity of experimental data(with the incoming Mach number from 0.50 to 2.86),Waveriders with large volume efficiency,CAV(common aero vehicle) with high lift-drag ratio,etc.During the flow field calculation,the divided-zone technology was adopted,which means employing the RANS method during the calculation of the whole flow field,but employing the DES analysis method only in the zone characterized by large-scale separation or severe separation.The numerical simulation of 63 cases of the six kinds of typical vehicles finished in this paper suggests:although employing the DES method only in the severely separated zone is not DES exactly,the numerical results (including results of aerodynamic force and aero thermal) of the flow field obtained in this way agree with the experimental data well and the efficiency of the flow field is higher than that obtained in the way applying DES in the whole flow field.
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[1] 陈懋章.黏性流体力学基础[M].北京:高等教育出版社,2002. [2] 王保国,蒋洪德,马晖扬,等.工程流体力学[M].北京:科学出版社,2011. [3] Anderson D A,Tannehill J C,Pletcher R H.Computational fluid mechanics and heat transfer[M].New York:Hemisphere,1984. [4] 王保国,黄虹宾.叶轮机械跨声速及亚声速流场的计算方法[M].北京:国防工业出版社,2000. [5] Harten A.High resolution schemes for hyperbolic conservation laws[J].J. Computational Phys.,1983,49:357-393. [6] Shu C W.Essentially non-oscillatory and weighted essentially nonoscillatory schemes for hyperbolic conservations laws.NASA CR 97-206253,1997. [7] 王保国,刘淑艳,黄伟光.气体动力学[M].北京:北京理工大学、北京航空航天大学、西北工业大学、哈尔滨工程大学、哈尔滨工业大学出版社,2005. [8] 王保国,吴俊宏,朱俊强.基于小波奇异分析的流场计算方法及应用[J].航空动力学报,2010,25(12):2728-2747. WANG Baoguo,WU Junhong,ZHU Junqiang.Method based on wavelet singularity analysis for complicated flow and its application[J].Journal of Aerospace Power,2010,25(12):2728-2747.(in Chinese) [9] Jameson A.Time dependent calculations using multigrid with application to unsteady flows past airfoils and wings.AIAA Paper 91-1596,1991. [10] 王保国,刘淑艳,张雅.非结构网格下非定常流场双时间步长加权ENO-强紧致杂交高分辨率格式[J].工程热物理学报,2005,26(6):941-943. WANG Baoguo,LIU Shuyan,ZHANG Ya.A new weighted ENO-strongly compact difference schemes and dual-time method for thesolution of the unsteady flows on unstructured grids[J].Journal of Engineering Thermophysics,2005,26(6):941-943.(in Chinese) [11] Anderson J D Jr.Hypersonic and high temperature gas dynamics [M].New York:McGraw-Hill,1989. [12] 王保国,黄伟光.高超声速气动热力学[M].北京:科学出版社,2011. [13] 王保国,黄伟光,钱耕.再入飞行中DSMC与Navier-Stokes两种模型的计算与分析[J].航空动力学报,2011,26(5):961-976. WANG Baoguo,HUANG Weiguang,QIAN Geng,et al.Computation and analysis of DSMC and Navier-Stokes model in reentry flight[J].Journal of Aerospace Power,2011,26(5):961-976.(in Chinese) [14] Smits A J,Dussauge J P.Turbulent shear layers in supersonic flow[M].New York:Springer,2006. [15] Pope S.Turbulent flows[M].Cambrige:Cambrige University Press,2000. [16] Lesieur M.Trubulence in fluids[M].New York:Kluwer Academic Publishers,1997. [17] Berselli L C,Iliescu T,Layton W J.Mathematics of large eddy simulation of turbulent flows[M].New York:Springer,2006. [18] Spalart P R,Jou W H,Stretlets M,et al.Comments on the feasibility of LES for wings,and on the hybrid RANS/LES approach //Proceedings of the 1st AFOSR International Conference on DNS/LES.Columbus:Greyden Press,1997:137-147. [19] Shur M L,Spalart P R,Strelets M K,et al.A hybrid RANS-LES approach with delayed-DES and wall-modelled LES capabilities[J].International Journal of Heat and Fluid Flow,2008,29(6):1638-1649. [20] 王保国,卞荫贵.关于三维Navier-Stokes方程的黏性项计算[J].空气动力学学报,1994,12(4):375-382. WANG Baoguo,BIAN Yingui.On numerical computation of viscous terms for 3-D Navier-Stokes equations[J].Acta Aerodynamica Sinica,1994,14(4):375-382.(in Chinese) [21] Hansen A,Sorensen N N,Johansen J.Detached-eddy simulation of decaying homogeneous isotropic trubulence.AIAA Paper 2005-885,2005. [22] 吴晶峰, 宁方飞.后台阶流动的Hybrid RANS/LES 模拟[J].北京航空航天大学学报,2011,37(6):701-704. WU Jingfeng,NING Fangfei.Hybrid RANS-LES method applied to backward facing step flow[J].Journal of Beijing University of Aeronautics and Astronautics,2011,37(6):701-704.(in Chinese) [23] 孙拓.几类复杂流动的数值计算及应用.北京:北京理工大学,2011. SUN Tuo.Numerical computation and appliance for complex fluid filed of three types.Beijing:Beijing Institute of Technology,2011.(in Chinese) [24] Spearman M L,Collins I K.Aerodynamic characteristics of a swept-wing cruise missile at Mach number from 0.50 to 2.86.NASA Technical Note D-7069,1972. [25] Stephens E.Afterbody heating data obtained from an atlas boosted mercury configuration in a free body reentry.NASA TM X-493,1961. [26] 郭洪福.五种典型高超声速飞行器流动的初步计算与分析.北京:北京理工大学,2011. GUO Hongfu.Preliminary computation and analysis of five kinds of typical hypersonic aircrafts.Beijing:Beijing Institute of Technology,2011.(in Chinese) [27] Kruse R L,Malcolm G N,Short B J.Comparison of free-flight measurements of stability of the Gemini and Mercury capsules at Mach numbers 3 and 9.5.NASA TM X-957,1964. [28] 王保国,李耀华,钱耕.四种飞行器绕流的三维DSMC计算与传热分析[J].航空动力学报,2011,26(1)1-20. WANG Baoguo,LI Yaohua,QIAN Geng.Three-dimensional DSMC calculation and heat transfer analysis of four capsules for hypersonic rarefied conditions[J].Journal of Aerospace Power,2011,26:1-20.(in Chinese) [29] 王保国,孙业萍,钱耕.两类典型高速飞行器壁面热流的工程算法 //龙升照,Dhillon B S.第10届人-机-环境系统工程大会论文集.美国,纽约:美国科研出版社,2010:299-305. WANG Baoguo,SUN Yeping,QIAN Geng.An engineering algorithm for wall heat flux of two typical hypersonic vehicles //Long Shengzhao,Dhillon B S.Proceedings of the 10th Conference on Man-Machine-Environment System Engineering.New York,USA:Scientific Research Publishing,USA,2010:299-305.(in Chinese) [30] 王保国,刘淑艳,王新泉,等.流体力学[M].北京:机械工业出版社,2011. [31] Slucomb T H.Project Fire Ⅱ afterbody temperatures and pressures at 11.35 kilometers per second.NASA TM X-1319,1966. [32] 安二.几种典型飞行器高超声速绕流的计算与壁面热流分析.北京理工大学,2011. AN Er.Several typical vehicle hypersonic flow calculation and wall heat flux analysis.Beijing:Beijing Institute of Technology,2011.(in Chinese) [33] 王保国,李翔,黄伟光.激波后高温高速流场中的传热特性研究[J].航空动力学报,2010,25(5):963-980. WANG Baoguo,LI Xiang,HUANG Weiguang.Analytical study of heat transfer of high-temperature and high-velocity flow field behind shock waves[J].Journal of Aerospace Power,2010,25(5):963-980.(in Chinese) [34] Papp J L,Dash S M.A rapid engineering approach to modeling hypersonic laminar to turbulent transitional flows for 2D and 3D geometries. AIAA 2008-2600,2008. [35] 卞荫贵,钟家康.高温边界层传热[M].北京:科学出版社,1986. [36] 卞荫贵,徐立功.气动热力学[M].合肥:中国科学技术大学出版社,1997.
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