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�������պ����ѧѧ�� 2005, Vol. 31 Issue (04) :477-480    DOI:
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1. �������պ����ѧ ���տ�ѧ�빤��ѧԺ, ���� 100083;
2. �й����������о��뷢չ����, �Ĵ����� 621000
Numerical investigation of supersonic jet interactions for tactical bodies
Deng Youqi1, Yan Chao1, Wu Xiaojun2, Zheng Ming2*
1. School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
2. China Aerodynamics Research and Development Center, Mianyang Sichuan 621000,China

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Abstract�� In order to investigation of the jet interaction for finned bodies, the interaction between a lateral jet and the supersonic external flow was investigated numerically by solving the N-S equation. To model more exactly the nozzle geometry and resolve the complex flow associated with the lateral jet problem,the multi-block point matched grid generation technique and "O" type grid technique were applied. The detailed numerical simulation for a variety of missile geometries in the supersonic flow was performed. These include nonfinned axisymmetrical bodies and finned bodies with either strakes or aft-mounted tail fins. The computations were performed at Mach numbers 2 and 4.5. The computational results show significant interactions of the jet induced flowfield with the fin surfaces that produce additional effects compared with the body alone. The computational results were compared with the experimental results from a previously published wind-tunnel study that consisted primarily of global force and moment measurements. The numerical calculations show good agreement with the experimental investigation at supersonic Mach numbers.
Keywords�� lateral jet   finite volume method   numerical simulation   complicated flow     
Received 2004-03-05;
Fund:

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About author: ������(1963-),��,����������,��ʿ��, cardcdyq@vip.sina.com.
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������, �ֳ�, ������, ֣��.ս����������������ֵģ��[J]  �������պ����ѧѧ��, 2005,V31(04): 477-480
Deng Youqi, Yan Chao, Wu Xiaojun, Zheng Ming.Numerical investigation of supersonic jet interactions for tactical bodies[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2005,V31(04): 477-480
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