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三维高超音速干扰流场数值模拟与实验验证
引用本文:李桦,王承尧,易仕和,程忠宇.三维高超音速干扰流场数值模拟与实验验证[J].国防科技大学学报,2001,23(4):13-15 ,31.
作者姓名:李桦  王承尧  易仕和  程忠宇
作者单位:国防科技大学航天与材料工程学院,
基金项目:湖南省自然科学基金资助项目 ( 99JJY2 0 0 5)
摘    要:采用Osher Chakraverthy的TVD格式、Baldwin Lomax湍流模型和LU SSOR隐式方法求解了完全NS方程 ,数值模拟了三维高超音速绕流与横向喷流干扰流场。并在高超音速炮风洞中开展了喷流实验研究 ,对该喷流流场的数值计算结果进行实验验证

关 键 词:三维高超音速干扰流场  数值模拟  实验验证
文章编号:1001-2486(2001)04-0013-03
收稿时间:2000/11/1 0:00:00
修稿时间:2000年11月1日

Numerical Simulation and Validation of 3D Hypersonic Jet Interaction Flowfield
LI Hu,WANG Chengyao,YI Shihe and CHENG Zhongyu.Numerical Simulation and Validation of 3D Hypersonic Jet Interaction Flowfield[J].Journal of National University of Defense Technology,2001,23(4):13-15 ,31.
Authors:LI Hu  WANG Chengyao  YI Shihe and CHENG Zhongyu
Affiliation:College of Aerospace and Materials Engineering , National Univ. of Defense Technology, Changsha 410073,China;College of Aerospace and Materials Engineering , National Univ. of Defense Technology, Changsha 410073,China;College of Aerospace and Materials Engineering , National Univ. of Defense Technology, Changsha 410073,China;College of Aerospace and Materials Engineering , National Univ. of Defense Technology, Changsha 410073,China
Abstract:A numerical method has been developed to solve the three dimensional Navier-Stokes equations and the numerical procedure uses Osher-Chakraverthy's TVD scheme for the inviscid flux and central difference scheme for the viscous flux. LU-SSOR method is used to solve the resulting systems of discretized equations and the Baldwin-Lomax turbulent model is used. Numerical solutions of three dimensional hypersonic jet interaction flow field with angle of attack of 5° is obtained and experimentally validated this numerical result at KD-01 gun wind tunnel. By validating, some problems of numerical simulation are studied.
Keywords:D hypersonic jet interaction flow field  numerical simulation  validation  
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