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

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

任超奇^1,2,
王强^1,2,
胡海洋¹

1. 北京航空航天大学能源与动力工程学院, 北京 100191;
2. 先进航空发动机协同创新中心, 北京 100191

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
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- 文章访问数: 1466
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- 被引次数: 0
出版历程
- 收稿日期: 2014-03-21
- 刊出日期: 2014-10-28

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

1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

摘要

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.
- 喷管-后体 /
- 试验优化设计 /
- 响应面法 /
- 流量系数 /
- 推力系数
Abstract: The aerodynamic characteristics of axisymmetric convergent-divergent nozzle and vehicle afterbody were studied. Based on the response surface method of orthogonal polynomials by combining with the self-programming, the three-dimensional flow field was numerically simulated. Flux coefficient and thrust coefficient were selected as the optimization indicators, while half convergence angle, throat radius, half expansion angle, bottom area and tail contraction angle were selected as the research objects to analyse under two conditions. By constructing and solving the function of response surface, the results show that half convergence angle and half expansion angle affect about 90% of aerodynamic characteristics; half convergence angle, throat radius and bottom area affect about 85% when discussing flux coefficient only; half expansion angle affect about 85% when discussing thrust coefficient only; half convergence angle, half expansion angle and throat radius affect more than 90% when discussing condition H=0km, Ma=0 only; half convergence angle and half expansion angle affect more than 85% when discussing condition H=20km, Ma=2 only.
- nozzle-afterbody /
- experiment optimization design /
- response surface method /
- flux coefficient /
- thrust coefficient

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参考文献(21)

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