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

^*Corresponding author for this work

School of Astronautics

Beihang University

Research output: Contribution to journal › Article › peer-review

2 Scopus citations

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.

Original language	English
Pages (from-to)	15-24
Number of pages	10
Journal	Tuijin Jishu/Journal of Propulsion Technology
Volume	19
Issue number	5
State	Published - 1998

Keywords

Engine nozzle
Hydrogen oxygen engine
Numerical simulation
Reaction kinetics
Viscous flow

Cite this

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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

Abstract

Keywords

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