航空学报英文模板

航空学报英文模板 Chinese Journal of Aeronautics 25 (2012) xx-xx Contents lists available at ScienceDirect Chinese Journal of Aeronautics journal homepage: www.elsevier.com/locate/cja Generation of Dynamic Grids and Computation of Unsteady Transonic Flows around Assemblies a,*bCAI Fei, ZHANG Liping aDepartment of Aerodynamics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China bSchool of Electronic and Information Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China,投 稿时请将作者姓名和单位删掉, (注:英文单位名称请注意写准确，具体可上本刊网站下载中心“单位英文名称”查询，如发现本刊所给英 译文有误，欢迎指正) Received 5 May 2009; revised 11 June 2009; accepted 16 September 2009 Abstract The coupled numerical simulation of flow field, solid temperature field, species concentration field and gas radiation trans-fer/ energy field based on statistical narrow-band correlated-k (SNBCK) model, is employed to accurately predict aerothermo- dynamic characteristic of aircraft exhaust system. A series of methods to increase computational efficiency and descend compu-tational resources make it possible to finish the calculation in PC. The parameters of narrow-band model are evaluated by HI-TEMP line-by-line database. Three examples have proved the accuracy of using these methods to solve flow heat transfer coupled problem and radiation transfer/energy equation, which are the calculation of temperature distribution of water-cooling nozzle in rocket engine, the calculation of carbon dioxide absorptivity at 4.3 micron band, and the gas radiation heat transfer evaluation of the cylindrical furnace. Finally, the inner flaps temperature distribution of ejecting nozzle with floating outer flaps is computed, under high-altitude, high-speed and afterburning conditions. Two completely different air-inlet schemes of eject-ing channel almost achieve the same effect in cooling inner flaps.(英文摘要应不少于150词;包含研究的目的、方法、结 果和结论;通常用一般现在时，除非有明显的过去时间指示词出现) Keywords: transonic flow; unsteady flow; full-potential equation(5-8个，建议其中1-2个选自EI controlled term 词表) achieved only on large computers, and moreover, the 1. Introduction [1]results are not ideal sometimes. A viscous/inviscid interaction method is an applicable one and the com-The computation method of unsteady transonic flow putation time can be reduced by two orders. based on N-S equations should be best accurate, but to The method to solve the full-potential equation over three-dimensional complex problems, it can be transonic unsteady forces on wings has been devel-[2-3] oped, but to assemblies, it is not mature, and the [4-5]*Corresponding author. Tel.: +86-10-82317058. research works are continuously carried on. E-mail address: abc@buaa.edu.cn The key to compute the unsteady aerodynamic Foundation item: National Natural Science Foundation of China (基金号) forces is to generate dynamic grids efficiently. In the (注:基金项目的正确英文名称请查询本刊下载中心“基金项目英文present paper, an algebraic method and rapid deform- 名称”) ing technique are used to generate three-dimensional 1000-9361/$ - see front matter ? 2011 Elsevier Ltd. All rights reserved. boundary-fitted dynamic grids for assemblies. The doi: ? 2 ? CAI Fei et al. / Chinese Journal of Aeronautics 24(2011) xx-xx No.2 conservative full-potential equation is solved by a plied to unsteady flows. As it will consume much time time-accurate approximate factorization algorithm to generate grids once a time-step, to aerodynamic and internal Newton iterations. An integral boundary elasticity movement of small amplitude, ordinarily, the layer method based on the dissipation integral is used grids are obtained by solving the balance equation to account for viscous effects. The computational re-based on last time-step, but that is still not economic. sults about unsteady transonic forces on wings, bodies Taking the incompressible potential flow round a and control surfaces are in agreement with experi-cylinder for example, the stream function is mental data. (前言一般不要放图、表、公式) 2,,aVrsin,,,, (2) ,,,r2. Computation Scheme ,, where a is radius, is the velocity of free stream. V,2.1. Governing equation Magnifying its radius to , then the previous a，, 2.1.1 Governing equation streamline passing point (r, , ) will yield a normal displacement ,r The unsteady full-potential equation written in a 2ra,，，body fitted coordinate system is given by (3) ,,,,,,r22ra， (1) ()()()()0,,,,JJJJ，，，,UVW,,,, That is difficulty directly to generate dynamic grids. where , is density, U, V, and W are the contravariant Simplifying further, the coordinates (represented by velocity components in the ,, ,, and , direc-subscript u) of the dynamic grids are tions,means time, and J is Jacobian. (正文中不要, (4) xxxx,,,,()gurrs用公式编辑器插入符号，直接敲入即可) where subscript s represents the boundary-fitted static 2,qUVW,,，,，,()()(),,,,,,grids which are used as the initial values, r represents ttt,,,,the instantaneous coordinate that the static grids move Uaaa,，，，,,,,,t111213,,, to with bodies, g is the function about the serial num-,Vaaa,，，，,,,,t122223,,,,ber of the grid lines. ,Waaa,，，，,,,,t132333,222,,,,,,,,,,,iijjkk,,,bbb,,g,max,, (5) ,,,,,,(公式编辑器中的行距不要改动，默认值即可) ,,iijjkk,,,fbfbfb,,,,,,,,(公式中用到小括号时，不要用公式编辑器中的括where b represents the corresponding boundary points, x号，如，直接用键盘敲入即可如) ()x，，f represents the far field points. where , is velocity potential. 3. Presentation of Result 2.2. Generation of grids F5 wing/missile and HARW wing/fuselage are tak- en for examples in the present paper. Fig.1 shows the The algebraic method is used to generate sketches of F5 wing/missile and HARW wing/fuselage three-dimensional boundary-fitted grids for a wing. with control surfaces. The missile is located at 73.5 The height of the first grid next to the body is con-percent of half-span. The trailing edge control surface trolled, and the grids near to the body are normalized. of HARW wing/fuselage takes up 20 percent of the To wing/missile combination, the H-H boundary- chord; control surface I is located at a position from fitted grids for a single wing are generated at first in 58.9% to 79.4% of half span; control surface II is lo-order to simulate the aerodynamic forces on missiles cated from 9.6% to 23.9%. Fig.2 is the H-H surface accurately. The section at the position of pylon is grids for F5 wing/missile. Fig.3 shows the overlooking changed into two overlapping layers. A partial de-view of HARW wing/fuselage assembles’ C-H grids. forming technique is used in the area of py- lon/launching/ missile to get the static grids for the combination. When with fuselage, the deforming technique is used at the symmetric section to get the static grids also. To simplify the equation, the dynamic grids where the far field is fixed and the body is dynamic are ap- No.2 CAI Fei et al. / Chinese Journal of Aeronautics 24(2011) xx-xx ? 3 ? particle impact noise detection testing. IEEE Proceed- ings Annual Reliablity and Maintainability Sympo- sium. 2004; 536-540.(会议论文) [5] Chadrasear R, Tiwari S N. Thermochemical nonequi- librium and radiative interactions in supersonic hy- drogen-air combustion. AIAA-1992-0340, 1992. (研 究 报告 软件系统测试报告下载sgs报告如何下载关于路面塌陷情况报告535n,sgs报告怎么下载竣工报告下载 ) [6] RTCA DO-245A. Minimum aviation systems per- formance standards for local area augmentation sys- tem(LAAS). Washington D.C.: RTCA Inc., 2004. (技 术 规范 编程规范下载gsp规范下载钢格栅规范下载警徽规范下载建设厅规范下载 或标准文献) [7] Barbante P E. Accurate and efficient modeling of Fig.4 Comparison between computation result and expe-high-tempera- ture nonequilibrium air flows. PhD the-[24]rimental data for temperature distribution of inner sis, von arman Institute for Fluid Dynamics, 2001.(学wall of nozzle. 位论文) [8] Aha D, Murphy P. UCI Repository of machine learn-Table 5 CPU time ratio of each term ing databases. <;. Irvine, CA: University of California, Department of Information Computational term CPU time/% and Computer Science, 1994.(电子文献) Flow field 32.6 [9] Khalifa H E, Glauser M N.Low-mixing nozzle for Solid temperature field 2.2 personal ventilation. US Provisional Patent Applica-Species concentration field 4.3 tion No.60/826,929, 2006.(专利文献) Radiation transfer/energy field 60.9 注意: 上述文献如为中文文献，则只需提供其英译 文，最后加上 “[in Chinese]”，其他格式同前。 4. Conclusions Biographies: ,投稿时请将作者简介删掉, (1) A rapid method of the generation of boun- dary-fitted dynamic grids is developed in this paper, LU Zhiliang received the B.S. and M.S. degrees in me- chanical engineering from Nanjing Aeronautical Institute in and the method of Viscous/Inviscid Interaction is used 1984 and 1987 respectively, and then became a teacher to compute the unsteady aerodynamic forces on there. His main research interests are …. wing/missiles and wing/body with control surfaces. E-mail: lulu213@yahoo.com.cn (2) The computation results are in agreement with experimental data. To unsteady flows, it takes nearly John SMITH is a Ph.D. student at school of automation, one hour to carry out three time cycles with 140 thou-Beihang University. He received his B.S. degree from Wu-sand nodes, so this method is powerful. This method han University in 2008. His area of research includes… presented in this paper provides an applicable, effi-E-mail: wuhanujogn@sina.com cient tool for the aerodynamic elasticity analysis in the Alice S.L. ZINOBER is a professor and Ph.D. supervisor transonic aspect. (分点 总结 初级经济法重点总结下载党员个人总结TXt高中句型全总结.doc高中句型全总结.doc理论力学知识点总结pdf ，只写结论，其他背景、at college of mechanical engineering, Cambridge University, 方法都不必赘述) Cambridge, U.K. She received the Ph.D. degree from the same university in 1970. Her current research interests References are… E-mail: lzlsax@jlonline.com [1] Matthews F L, Rawlings R D. Composite materials engineering and science. 2nd ed. New York: Chapman & Hall, 1994.(专著) Appendix [2] Soutis C, Fleck N A. Static compression failure of carbon fibre T800/924C composite plate with single hole. Journal of Composite Materials 1990; 24(5): 内容为10号字 536-538.(期刊论文) [3] Bassler H J, Eifler D. Characterisation of plasticity induced martensite formation during fatigue of auste- nitic steel. In: Rie K T, Portella P D. Low-cycle Fati- gue and Elasto-plastic Behaviour of Materials. Ams- terdam: Elsevier Sci Ltd, 1998; 235-240.(专著中的部 分文献) [4] Prairie R R, Zimmer W J. Statistical modeling for 动态网格快速生成及组合体跨声速非定常气动力计算 ? 4 ? CAI Fei et al. / Chinese Journal of Aeronautics 24(2011) xx-xx No.2 蔡斐，张利平 浮动外调节片引射喷管内调节片温度分布。两种完全 (南京航空航天大学空气动力学系) 不同的引射通道进气 方案 气瓶 现场处置方案 .pdf气瓶 现场处置方案 .doc见习基地管理方案.doc关于群访事件的化解方案建筑工地扬尘治理专项方案下载 对内调节片的冷却效果几乎 相同。 摘 要: 耦合求解流场、固体温度场、组分浓度场、关键词: 跨声速流; 非定常流; 全位势方程; 组合体 基于统计窄带关联k(SNBCK)模型的气体辐射传输/ 能量方程以求准确模拟飞行器排气系统气动热力特注:最后的中文翻译会连同英文一起在清华同方数据性。通过一系列提高计算效率降低计算资源占用的算库中进行检索，所以要求中文的 题 快递公司问题件快递公司问题件货款处理关于圆的周长面积重点题型关于解方程组的题及答案关于南海问题 目、作者、作者单法，使在PC机上完成上述计算成为可能。窄带模型位、摘要、关键词与英文一一对应。 参数由HITEMP逐线计算数据库计算得到。通过火箭 发动机水冷喷管壁温分布计算，圆柱炉膛辐射换热特 ,投稿时如按此模板写作～请勿加上中文摘要,性计算，CO 4.3,m波段吸收率计算3个算例分别验2 证了所采用程序求解流热耦合问题、辐射能量/传输方 程的准确性。最后计算了飞行器高空高速加力状态下