Numerical simulation of reacting viscous flow in nozzle

Huazhao Zhang; Guozhu Liang; Huiyu Wang

Numerical simulation of reacting viscous flow in nozzle

Huazhao Zhang^*
, Guozhu Liang
, Huiyu Wang

^*此作品的通讯作者

宇航学院

Beihang University

科研成果: 期刊稿件 › 文章 › 同行评审

2 引用（Scopus）

摘要

The viscous reacting flowfield in the O₂/H₂ rocket engine nozzle was computed by using time-depenent explicit difference scheme. The combustion process was modeled by a 6-specice, 8-step finite-rate chemical model, and the Baldwin-Lomax algebric turbulent model was adopted. The distribution of flow parameters and mass fractions of products were presented. The results show that the explicit difference scheme is feasible in calculating the viscous reacting flows.

源语言	英语
页（从-至）	15-24
页数	10
期刊	Tuijin Jishu/Journal of Propulsion Technology
卷	19
期	5
出版状态	已出版 - 1998

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引用此

@article{797d419374034a26903aa5d4edc0455a,

title = "Numerical simulation of reacting viscous flow in nozzle",

abstract = "The viscous reacting flowfield in the O2/H2 rocket engine nozzle was computed by using time-depenent explicit difference scheme. The combustion process was modeled by a 6-specice, 8-step finite-rate chemical model, and the Baldwin-Lomax algebric turbulent model was adopted. The distribution of flow parameters and mass fractions of products were presented. The results show that the explicit difference scheme is feasible in calculating the viscous reacting flows.",

keywords = "Engine nozzle, Hydrogen oxygen engine, Numerical simulation, Reaction kinetics, Viscous flow",

author = "Huazhao Zhang and Guozhu Liang and Huiyu Wang",

year = "1998",

language = "英语",

volume = "19",

pages = "15--24",

journal = "Tuijin Jishu/Journal of Propulsion Technology",

issn = "1001-4055",

publisher = "China Aerospace Science and Industry Corp",

number = "5",

}

TY - JOUR

T1 - Numerical simulation of reacting viscous flow in nozzle

AU - Zhang, Huazhao

AU - Liang, Guozhu

AU - Wang, Huiyu

PY - 1998

Y1 - 1998

N2 - The viscous reacting flowfield in the O2/H2 rocket engine nozzle was computed by using time-depenent explicit difference scheme. The combustion process was modeled by a 6-specice, 8-step finite-rate chemical model, and the Baldwin-Lomax algebric turbulent model was adopted. The distribution of flow parameters and mass fractions of products were presented. The results show that the explicit difference scheme is feasible in calculating the viscous reacting flows.

AB - The viscous reacting flowfield in the O2/H2 rocket engine nozzle was computed by using time-depenent explicit difference scheme. The combustion process was modeled by a 6-specice, 8-step finite-rate chemical model, and the Baldwin-Lomax algebric turbulent model was adopted. The distribution of flow parameters and mass fractions of products were presented. The results show that the explicit difference scheme is feasible in calculating the viscous reacting flows.

KW - Engine nozzle

KW - Hydrogen oxygen engine

KW - Numerical simulation

KW - Reaction kinetics

KW - Viscous flow

UR - https://www.scopus.com/pages/publications/0347602801

M3 - 文章

AN - SCOPUS:0347602801

SN - 1001-4055

VL - 19

SP - 15

EP - 24

JO - Tuijin Jishu/Journal of Propulsion Technology

JF - Tuijin Jishu/Journal of Propulsion Technology

IS - 5

ER -

Numerical simulation of reacting viscous flow in nozzle

摘要

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