NUMERICAL SIMULATION OF SUPERSONIC AXISYMMETRIC FLOW OVER MISSILE AFTERBODY WITH JET EXHAUST USING POSITIVE SCHEMES  

弹尾超声速轴对称喷流的正格式数值模拟(英文)

作　　者：朱孙科[1] 马大为[1] 陈二云[2] 乐贵高[1] 

机构地区：[1]南京理工大学机械工程学院 [2]上海理工大学能源与动力学院

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2011年第3期255-261,共7页南京航空航天大学学报（英文版）

基　　金：Supported by the National Natural Defense Basic Scientific Research Program of China(A262006-1288);the Key Disciplines Program of Shanghai Municipal Commission of Education(J50501)~~

摘　　要：Supersonic axisymmetric jet flow over a missile afterbody containing exhaust jet is simulated using the second order accurate positive schemes method developed for solving the axisymmetric Euler equations based on the 2-D conservation laws.Comparisons between the numerical results and the experimental measurements show excellent agreements.The computed results are in good agreement with the numerical solutions obtained by using third order accurate RKDG finite element method.The results show larger gradient at discontinuous points compared with those obtained by second order accurate TVD schemes.It indicates that the presented method is efficient and reliable for solving the axisymmetric jet with external freestream flows,and shows that the method captures shocks well without numerical noise.采用二阶正格式方法对超声速轴对称喷流流动进行数值模拟。将二维守恒方程的正格式方法发展到轴对称Euler方程组的求解,并对导弹尾部超声速伴随射流进行了数值计算。数值结果与实验照片所反映的流动特征吻合较好,与三阶精度间断有限元方法计算结果吻合,相比于二阶高分辨率TVD格式的计算结果,正格式方法的计算结果在间断点处具有较大的梯度变化。这表明该方法对激波具有较强的捕捉能力,在间断处不会出现数值振荡,对弹尾声音速伴随射流的数值模拟真实、有效。

关 键 词：computational fluid dynamics supersonic flow positive schemes numerical simulation 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]