| 引用本文: | 李桦,王承尧,易仕和,等.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.[点击复制] |
| LI Hua,WANG Chengyao,YI Shihe,et al.Numerical Simulation and Validation of 3D Hypersonic Jet Interaction Flowfield[J].Journal of National University of Defense Technology,2001,23(4):13-15 ,31[点击复制] |
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| 三维高超音速干扰流场数值模拟与实验验证 |
| 李桦, 王承尧, 易仕和, 程忠宇 |
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(国防科技大学 航天与材料工程学院, 湖南 长沙 410073)
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| 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 |
| DOI： |
| 投稿日期：2000-11-01 |
| 基金项目:湖南省自然科学基金资助项目（99JJY2005） |
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| Numerical Simulation and Validation of 3D Hypersonic Jet Interaction Flowfield |
| LI Hua, WANG Chengyao, YI Shihe, CHENG Zhongyu |
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(College of Aerospace and Materials Engineering , National Univ. of Defense Technology, Changsha 410073,China)
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| 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: 3D hypersonic jet interaction flow field numerical simulation validation |
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