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Journal of Projectiles, Rockets, Missiles and Guidance >

2011 , Vol. 31 >Issue 5: 125 - 128

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2011.05.028

ROCKETS TECHNOLOGY

Numerical Simulation Research on Nozzle Performance of Scramjet

  • WEN Ke ,
  • LI Xuchang ,
  • MA Cenrui ,
  • SONG Yafei ,
  • HE Zhilin
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  • The Missile Institute, Air Force Engineering University, Shaanxi Sanyuan 713800, China

Received date: 2010-12-23

  Online published: 2025-05-30

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Abstract

The nozzle is an important component for thrust produced by scramjet engine. The flow field numerical simulation was conducted in NASA single expansion ramp nozzle experiment model. The flow field within nozzle was simulated using the Fluent CFD code which employed RNG k-e turbulence model to study the effect of the inlet parameters including specific heat ratio, NPR, Mach number, temperature, which showed the internal flow field's diversification rule and performance changed with various flow parameters of nozzle. The results are useful for further integrated design of scramjet combustor/nozzle.

Key words： scramjet; single expansion ramp nozzle; performance research; numerical simulation

Cite this article

WEN Ke , LI Xuchang , MA Cenrui , SONG Yafei , HE Zhilin . Numerical Simulation Research on Nozzle Performance of Scramjet[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2011 , 31(5) : 125 -128 . DOI: 10.15892/j.cnki.djzdxb.2011.05.028

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References

[1]
Eric Gamble，Dan Haid. Improving off-design nozzle performance using fluidic inje-ction,AIAA 2004-1206[R].2004.
[2]
Bardford J E. Rapid prediction of after body nozzle per formance in SCCREAM,AIAA 2002-3605[R].2002.
[3]
Engbolm W A. Numerical predictions of SERN performance using WNID code, AIAA 2003-4410[R]. 2003.
[4]
P Perrier, M Rapuc, P Rostand. Nozzle and afterbody design for hypersonic airbreathing vehicles, AIAA 1996-4548[R]. 1996.
[5]
T A Gronland, J L Cambier. Sensitivity to physical modeling for nozzle/afterbody flowfields, AIAA 1996-4547[R]. 1196.
[6]
晏至辉, 刘卫东. 超燃冲压发动机尾喷管数值分析[J]. 导弹与航天运载技术, 2006(5): 50-52.
[7]
张艳慧, 徐惊雷, 张堃元. 超燃冲压发动机非对称喷管设计点性能[J]. 推进技术, 2007, 28(3): 282-286.
[8]
徐惊雷, 张艳慧, 张堃元. 超燃冲压发动机非对称喷管非设计点性能计算[J]. 推进技术, 2007, 28(3): 287-290.
[9]
汪维娜, 王占学, 乔渭阳. 单斜面膨胀喷管几何参数对流场和性能的影响[J]. 航空动力学报, 2006, 21(2): 280-284.
[10]
李念, 张堃元, 徐惊雷. 二维非对称喷管数值模拟与验证[J]. 航空动力学报, 2004, 19(6): 802-805.
[11]
刘陵, 刘敬华, 张榛,等. 超声速燃烧和超声速燃烧冲压发动机[M]. 西安: 西北工业大学出版社, 1993.
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