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弹箭与制导学报 >

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

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

火箭技术

超燃冲压发动机尾喷管性能数值模拟研究

  • 文科 ,
  • 李旭昌 ,
  • 马岑睿 ,
  • 宋亚飞 ,
  • 何至林
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  • 空军工程大学导弹学院,陕西三原 713800

文科(1987-),男,陕西周至人,硕士研究生,研究方向:发动机内流场仿真与计算。

收稿日期: 2010-12-23

  网络出版日期: 2025-05-30

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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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摘要

尾喷管是超燃冲压发动机产生推力的一个重要部件。文中以NASA单膨胀斜面喷管试验为参考,利用计算流体力学软件Fluent,采用RNGk-ɛ湍流模型,对尾喷管流场进行了数值模拟,研究了入口气流状态参数(比热比、静压比、马赫数、温度)对超燃冲压发动机尾喷管性能的影响,初步给出了尾喷管内流场特征以及性能随不同入口气流状态参数变化规律,为超燃冲压发动机尾喷管与燃烧室一体化设计提供一定理论参考。

关键词： 超燃冲压发动机; 单膨胀斜面喷管; 性能研究; 数值模拟

本文引用格式

文科 , 李旭昌 , 马岑睿 , 宋亚飞 , 何至林 . 超燃冲压发动机尾喷管性能数值模拟研究[J]. 弹箭与制导学报, 2011 , 31(5) : 125 -128 . DOI: 10.15892/j.cnki.djzdxb.2011.05.028

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

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参考文献

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