Influence of operating conditions on temperature distributions of exhaust plume of solid rocket motor

Wei Chen Wang; Shi Peng Li; Qiao Zhang; Ning Fei Wang; Chang Jian Wang; Yi Xu

Influence of operating conditions on temperature distributions of exhaust plume of solid rocket motor

Wei Chen Wang^*, Shi Peng Li, Qiao Zhang, Ning Fei Wang, Chang Jian Wang, Yi Xu

^*Corresponding author for this work

School of Aerospace Engineering

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

5 Citations (Scopus)

Abstract

A coupling calculation model for infrared radiation transfer of plume is built. The radiation source term is induced into energy equation, thus the plume flow field and radiation transfer can be solved in couple. A finite rate model is used to simulate the afterburning phenomenon; a discrete coordinate method is used to solve the radiation transfer equation. The spectral radiation intensity from 1000 cm ^-1 to 4500 cm ^-1 and the radiation intensity contours are obtained. The calculation results concide well with the experiment data. It shows that the motor's operation pressure, the free stream's Mach number and flight height can change the flow structure and temperature distributions of the plume in a extent.

Original language	English
Pages (from-to)	1493-1498
Number of pages	6
Journal	Binggong Xuebao/Acta Armamentarii
Volume	32
Issue number	12
Publication status	Published - Dec 2011

Keywords

Afterburning chemistry reaction
Coupled solution
Exhaust plume
Infrared radiation
Operating conditions
Propulsion system of aviation and aerospace
Solid motor

Cite this

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title = "Influence of operating conditions on temperature distributions of exhaust plume of solid rocket motor",

abstract = "A coupling calculation model for infrared radiation transfer of plume is built. The radiation source term is induced into energy equation, thus the plume flow field and radiation transfer can be solved in couple. A finite rate model is used to simulate the afterburning phenomenon; a discrete coordinate method is used to solve the radiation transfer equation. The spectral radiation intensity from 1000 cm -1 to 4500 cm -1 and the radiation intensity contours are obtained. The calculation results concide well with the experiment data. It shows that the motor's operation pressure, the free stream's Mach number and flight height can change the flow structure and temperature distributions of the plume in a extent.",

keywords = "Afterburning chemistry reaction, Coupled solution, Exhaust plume, Infrared radiation, Operating conditions, Propulsion system of aviation and aerospace, Solid motor",

author = "Wang, {Wei Chen} and Li, {Shi Peng} and Qiao Zhang and Wang, {Ning Fei} and Wang, {Chang Jian} and Yi Xu",

year = "2011",

month = dec,

language = "English",

volume = "32",

pages = "1493--1498",

journal = "Binggong Xuebao/Acta Armamentarii",

issn = "1000-1093",

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T1 - Influence of operating conditions on temperature distributions of exhaust plume of solid rocket motor

AU - Wang, Wei Chen

AU - Li, Shi Peng

AU - Zhang, Qiao

AU - Wang, Ning Fei

AU - Wang, Chang Jian

AU - Xu, Yi

PY - 2011/12

Y1 - 2011/12

N2 - A coupling calculation model for infrared radiation transfer of plume is built. The radiation source term is induced into energy equation, thus the plume flow field and radiation transfer can be solved in couple. A finite rate model is used to simulate the afterburning phenomenon; a discrete coordinate method is used to solve the radiation transfer equation. The spectral radiation intensity from 1000 cm -1 to 4500 cm -1 and the radiation intensity contours are obtained. The calculation results concide well with the experiment data. It shows that the motor's operation pressure, the free stream's Mach number and flight height can change the flow structure and temperature distributions of the plume in a extent.

AB - A coupling calculation model for infrared radiation transfer of plume is built. The radiation source term is induced into energy equation, thus the plume flow field and radiation transfer can be solved in couple. A finite rate model is used to simulate the afterburning phenomenon; a discrete coordinate method is used to solve the radiation transfer equation. The spectral radiation intensity from 1000 cm -1 to 4500 cm -1 and the radiation intensity contours are obtained. The calculation results concide well with the experiment data. It shows that the motor's operation pressure, the free stream's Mach number and flight height can change the flow structure and temperature distributions of the plume in a extent.

KW - Afterburning chemistry reaction

KW - Coupled solution

KW - Exhaust plume

KW - Infrared radiation

KW - Operating conditions

KW - Propulsion system of aviation and aerospace

KW - Solid motor

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SN - 1000-1093

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JO - Binggong Xuebao/Acta Armamentarii

JF - Binggong Xuebao/Acta Armamentarii

IS - 12

ER -

Influence of operating conditions on temperature distributions of exhaust plume of solid rocket motor

Abstract

Keywords

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