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收-扩喷管与飞行器后体的一体化气动优化设计

任超奇 王强 胡海洋

任超奇, 王强, 胡海洋. 收-扩喷管与飞行器后体的一体化气动优化设计[J]. 航空动力学报, 2014, (10): 2294-2302. doi: 10.13224/j.cnki.jasp.2014.10.004
引用本文: 任超奇, 王强, 胡海洋. 收-扩喷管与飞行器后体的一体化气动优化设计[J]. 航空动力学报, 2014, (10): 2294-2302. doi: 10.13224/j.cnki.jasp.2014.10.004
REN Chao-qi, WANG Qiang, HU Hai-yang. Integrated aerodynamic optimization design of convergent-divergent nozzle and vehicle afterbody[J]. Journal of Aerospace Power, 2014, (10): 2294-2302. doi: 10.13224/j.cnki.jasp.2014.10.004
Citation: REN Chao-qi, WANG Qiang, HU Hai-yang. Integrated aerodynamic optimization design of convergent-divergent nozzle and vehicle afterbody[J]. Journal of Aerospace Power, 2014, (10): 2294-2302. doi: 10.13224/j.cnki.jasp.2014.10.004

收-扩喷管与飞行器后体的一体化气动优化设计

doi: 10.13224/j.cnki.jasp.2014.10.004
详细信息
    作者简介:

    任超奇(1987- ),男,山西长治人,博士生,主要从事进排气系统、红外隐身研究.

  • 中图分类号: V275

Integrated aerodynamic optimization design of convergent-divergent nozzle and vehicle afterbody

  • 摘要: 以轴对称收-扩喷管与飞行器后体的气动特性为研究对象,基于部分正交多项式的响应面法结合自编程序进行了三维流场的数值模拟.选取流量系数和推力系数为优化指标,选取收敛半角、喉道半径、扩张半角、底部面积和尾部收缩角为研究对象,在两种工况下进行了分析.通过响应面函数的构造及求解,结果表明:扩张半角和收敛半角对气动性能的影响程度约为90%;只考虑流量系数时,收敛半角、喉道半径和底部面积的影响程度约为85%;只考虑推力系数时,扩张半角的影响程度约为85%;只考虑H=0km,Ma=0工况时,扩张半角、收敛半角和喉道半径的影响程度达到90%以上;只考虑H=20km,Ma=2工况时,扩张半角和收敛半角的影响程度达到85%以上.

     

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出版历程
  • 收稿日期:  2014-03-21
  • 刊出日期:  2014-10-28

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