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高超声速飞行器-进气道一体化热流数值计算

丁海河 王发民

丁海河, 王发民. 高超声速飞行器-进气道一体化热流数值计算[J]. 航空动力学报, 2007, 22(8): 1297-1302.
引用本文: 丁海河, 王发民. 高超声速飞行器-进气道一体化热流数值计算[J]. 航空动力学报, 2007, 22(8): 1297-1302.
DING Hai-he, WANG Fa-min. Hypersonic vehicle-inlet integrated aeroheating simulation[J]. Journal of Aerospace Power, 2007, 22(8): 1297-1302.
Citation: DING Hai-he, WANG Fa-min. Hypersonic vehicle-inlet integrated aeroheating simulation[J]. Journal of Aerospace Power, 2007, 22(8): 1297-1302.

高超声速飞行器-进气道一体化热流数值计算

基金项目: 国家自然科学重点基金(90505016)资助项目

Hypersonic vehicle-inlet integrated aeroheating simulation

  • 摘要: 采用CFD(计算流体动力学)技术, 开展了飞行器前体/发动机一体化气动热环境分析.对层流区、转捩区和湍流区分别采用计算模型, 在湍流区利用压缩性修正的SSGZ-Jk-ε湍流模型, 在转捩区引入代数型转捩因子模型描述边界层由层流逐渐过渡为完全湍流的流动过程.计算了前体和内通道的表面热流, 并与实验结果进行了对比.结果表明所采用的计算方法可以较好地预测前体及发动机内通道热流率, 流动状态、几何结构及激波入射对热流值影响较大.

     

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出版历程
  • 收稿日期:  2006-07-31
  • 修回日期:  2006-10-12
  • 刊出日期:  2007-08-28

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