Numerical simulation on effects of variable specific heat capacity on internal flow field of jet vector nozzle

SONG Ya-fei; GAO Feng; WEN Ke; HE Zhi-lin; JIN Nan-nan

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Numerical simulation on effects of variable specific heat capacity on internal flow field of jet vector nozzle

更新时间：2026-07-07

- Numerical simulation on effects of variable specific heat capacity on internal flow field of jet vector nozzle
- Vol. 26, Issue 9, (2011)
- 作者机构：
  
  空军工程大学导弹学院,陕西三原,713800
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2011
- 稿件说明：
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SONG Ya-fei, GAO Feng, WEN Ke, et al. Numerical simulation on effects of variable specific heat capacity on internal flow field of jet vector nozzle[J]. 2011, 26(9).
DOI：

SONG Ya-fei, GAO Feng, WEN Ke, et al. Numerical simulation on effects of variable specific heat capacity on internal flow field of jet vector nozzle[J]. 2011, 26(9). DOI：

摘要

利用时间推进的有限体积法求解二维雷诺平均Navier-Stokes(N-S)方程

分别在变比热容和定比热容的情况下研究了射流推力矢量喷管的内流性能

并对两种情况下计算结果进行了比较.结果表明

与定比热容情况相比

工质为变比热容的燃气时

喷管内部由二次流产生的斜激波位置向喷管下游移动

回流区减小

喷管的推力矢量角和推力系数减小

温度越高

两种方法的计算结果相差越大.因此

在采用计算流体力学(computational fluidic dynamic

简称CFD)方法研究射流推力矢量喷管内流场性能时应该考虑变比热的影响.

Abstract

Given certain variable specific heat capacity and constant specific heat capacity

two-dimensional Reynolds average Navier-Stokes equation was solved by using time marching method in finite volume

and the internal flow of jet vector nozzle was studied.The results gained from different cases were compared.The results show that:as compared with the specific heat capacity

when the shock wave generated by second injection moves toward downstream divergent section

the thrust vector angle and thrust coefficient decrease.With the increase of temperature

the gap between the results from two methods became wider.The influence of variable specific heat capacity must be take into consideration when studying the internal flow field of jet vector nozzle by the method of computational fluidic dynamic.

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Related Author

Yunfeng LI

Kangqing DENG

Ruihua LU

Peiwen QIN

Chunliang GUO

Lifan YAN

Changlong HUANG

QIN Ya-xin

Related Institution

Key Laboratory of Aerospace Chemical Power Technology， Hubei Institute of Aerospace Chemical Techologh， China Aerospace Science and Technology Corporation，Xiangyang Hubei

Hubei Institute of Aerospace Chemistry Technology， China Aerospace Science and Technology Corporation，Xiangyang Hubei

National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

th Dept., Northwest Polytechnic University

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