稀薄流中基于碰撞分子特定次序的DSMC改进方法
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摘要
针对高超声速弹箭前方绕流流场中气体分子间碰撞导致复杂化学反应的问题,提出了一种化学反应类型取决于碰撞分子特定次序的DSMC(direct simulation Monte Carlo)改进方法。在变径硬球模型、Larsen-Borgnakke唯象论模型和Bird的化学反应概率模型的基础上,先取五组元(N2,O2,N,O,NO)混合气体间的离解、置换和复合反应为主要化学反应类型,采用Fortran语言编制了气体分子化学反应的DSMC源程序,模拟了高超声速二维圆柱绕流,并将模拟结果与有关文献中的理论数据进行了比较,在80 km,85 km,90 km处,圆柱表面处的热流系数峰值误差分别为1.1%,2.0%和1.9%,数值结果验证了该方法的可行性和合理性。
In order to solve the complex chemical reactions caused by the collision molecules in rarefield flow regime around the hypersonic projectile,a modified direct simulation Monte Carlo( DSMC) method depending on the specific sequence of the collision molecules was proposed. Based on the variable hard-spere model,the Larsen-Borgnakke phenomenological model and the chemical reaction model of Bird,the dissociation,displacement and reconbination reaction in five-species mixed gas( N2,O2,N,O,NO) were chosen as the main chemical reaction types,and the DSMC code was produced by using Fortran.Gas-molecular chemical reaction in hypersonic two-dimensional flow around a cylinder was simulated,and the results were compared with the theoretical data. At 80 km,85 km and 90 km,the error of the peak value of heat-flow coefficient at the surface of the cylinder is 1. 1%,2. 0% and 1. 9%,respectively. The numerical results verify the feasibility and rationality of the proposed method.
In order to solve the complex chemical reactions caused by the collision molecules in rarefield flow regime around the hypersonic projectile,a modified direct simulation Monte Carlo( DSMC) method depending on the specific sequence of the collision molecules was proposed. Based on the variable hard-spere model,the Larsen-Borgnakke phenomenological model and the chemical reaction model of Bird,the dissociation,displacement and reconbination reaction in five-species mixed gas( N2,O2,N,O,NO) were chosen as the main chemical reaction types,and the DSMC code was produced by using Fortran.Gas-molecular chemical reaction in hypersonic two-dimensional flow around a cylinder was simulated,and the results were compared with the theoretical data. At 80 km,85 km and 90 km,the error of the peak value of heat-flow coefficient at the surface of the cylinder is 1. 1%,2. 0% and 1. 9%,respectively. The numerical results verify the feasibility and rationality of the proposed method.
引文
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[2]王勇,王学德,许国龙.超音速弹丸高空流场数值模拟与稀薄气体效应研究[J].兵器装备工程学报,2016,37(10):13-18.WANG Yong,WANG Xuede,XU Guolong.Numerical simulation and rarefield gas effect of supersonic warhead in high flow field[J].Journal of Ordance Equipment Engineering,2016,37(10):13-18.(in Chinese)
[3]BIRD G A.Molecular gas dynamics and the direct simulation of gas flow[M].Oxford:Clarendon Press,1994.
[4]BIRD G A.Application of the DSMC method to the full shuttle geometry:AIAA 90-1962[R].Seattle,WA:AIAA,1990.
[5]吴其芬,陈伟芳.高温稀薄气体热化学非平衡流动的DSMC方法[M].长沙:国防科技大学出版社,1999.WU Qifen,CHEN Weifang.The DSMC method for the thermochemical nonequilibrium flows of high temperature rarefied gas[M].Changsha:National University of Defense Technology Press,1999.(in Chinese)
[6]王保国,李学东,刘淑艳.高温高速稀薄流的DSMC算法与流场传热分析[J].航空动力学报,2010,25(6):1203-1220.WANG Baoguo,LI Xuedong,LIU Shuyan.DSMC algorithm and heat transfer analysis of high temperature and high velocity rarefied gas flow[J].Journal of Aerospace Power,2010,25(6):1203-1220.(in Chinese)
[7]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-dimension DSMC calculation and heat tranfer analysis of four capsules for hypersonic rarefied conditions[J].Journal of Aerospace Porwer,2011,26(1):1-20.(in Chinese)
[8]石于中,陈伟芳,任兵,等.稀薄流热化学非平衡效应的DSMC研究[J].空气动力学报,1997,15(2):238-243.SHI Yuzhong,CHEN Weifang,REN Bing,et al.DSMC study for the effects of thermochemical nonequilibrium on rarefied flow[J].Acta Aerodynamica Sinica,1997,15(2):238-243.(in Chinese)
[9]樊菁,沈青.过渡领域高超声速圆柱绕流直接模拟[J].空气动力学报,1995,13(4):405-413.FAN Jing,SHEN Qing.The DSMC of hypersonic nonequilibrium flow past a circular cylinder in transional regime[J].Acta Aerodynamica Sinica,1995,13(4):405-413.(in Chinese)
[10]杨浩森,张斌,刘洪,等.DSMC热化学模拟分子数对氮氧离解反应计算影响分析[J].空气动力学报,2014,32(4):511-517.YANG Haosen,ZHANG Bin,LIU Hong,el at.Influence of the molecule number on nitrogen-oxygen dissociation reacting flows in DSMC simulations[J].Acta Aerodynamica Sinica,2014,32(4):511-517.(in Chinese)
[11]白海波.FORTRAN程序设计权威指南[M].北京:机械工业出版社,2013.BAI Haibo.Authoritative guide on FORTRAN program designing[M].Beijing:China Machine Press,2013.(in Chinese)
[12]王学德.高超声速稀薄气流非结构网格DSMC及并行算法研究[D].南京:南京航空航天大学,2006.WANG Xuede.The implementation of DSMC method on unstructured grids and parallel algorithm for hypersonic rarefied airflow[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2006.(in Chinese)