燃气流场算法程序实现及对比  

Development and Comparison of Gas Flow Field Program Using Different Schemes

作　　者：王帅 陈劲松[1] Wang Shuai;Chen Jin-song(Beijing Institute of Space Launch Technology, Beijing, 100076)

机构地区：[1]北京航天发射技术研究所,北京100076

出　　处：《导弹与航天运载技术》2018年第6期90-95,115,共7页Missiles and Space Vehicles

基　　金：重型运载火箭发射喷流噪声及喷水降噪机理研究项目(51741602)

摘　　要：为了对常用计算格式进行对比,选取更适合燃气流场模拟的计算格式,采用有限体积Roe格式、AUSM+格式与NND格式开发了燃气流场计算程序,并通过二维前台阶激波反射算例验证了程序计算结果的可靠性。在此基础上得到了三维喷管燃气内流场和自由喷流外流场的仿真计算结果。得到了3种格式计算结果在规律上具有一致性,表现出了良好的数值稳定性和激波捕捉能力;在燃气流场的模拟中,6种格式细节上存在差异:AUSM+格式在流动边界处易产生数值振荡,而NND格式在压力出口边界附近存在数值振荡;由于6种格式数值耗散不同,在喷管径向数值变化幅度上也存在差异的结论。Based on the finite volume Roe scheme,AUSM+scheme and NND scheme,the gas flow field calculation program is developed.The two-dimensional step flow field simulation results are in agreement with the literature result,which proves the correctness of the results.Then three-dimensional flow field of the rocket motor nozzle and free jet are simulated.The simulation results show the same regularity and reflect the flow characteristics of the gas flow field.There are subtle differences between the three scheme:AUSM+scheme has numerical oscillation near the flow boundary,while NND scheme has numerical oscillation near the pressure outlet,the cause of oscillation is analyzed according to the characteristics of the schemes.Because of the difference in numerical dissipation of the three scheme,there is also a difference in the variation range along the radial.

关 键 词：燃气流场 数值模拟 Roe格式 AUSM+格式 NND格式 

分 类 号：V411.3[航空宇航科学与技术—航空宇航推进理论与工程]