Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor

Hui Tian; Guo Biao Cai; Zai Yong Sun

Computation of nozzle two-phase flow in a N₂O/HTPB hybrid rocket motor

Hui Tian^*
, Guo Biao Cai
, Zai Yong Sun

^*Corresponding author for this work

School of Astronautics

China Aerospace Science and Industry Corporation

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

9 Scopus citations

Abstract

Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide (N₂O)/hydroxyl-terminated polybutadiene CHTPB) based fuels hybrid rocket motor. MacCormack decomposition scheme and B-L algebraic turbulence model and two-phase equilibrium flow model were used. The nozzle flow and performance under three oxidizer-to-fuel ratios and four nozzle types were calculated. Effect of oxidizer-to-fuel ratio and nozzle type on nozzle performance was analyzed from the two-phase and gas phase results. Vacuum specific impulse is bound up with oxidizer-to-fuel ratio. This paper will be useful for the hybrid rocket motor design.

Original language	English
Pages (from-to)	1146-1150
Number of pages	5
Journal	Hangkong Dongli Xuebao/Journal of Aerospace Power
Volume	23
Issue number	6
State	Published - Jun 2008

Keywords

HTPB-based fuels
Hybrid rocket motor
NO
Nozzle
Two-phase flow

Cite this

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title = "Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor",

abstract = "Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide (N2O)/hydroxyl-terminated polybutadiene CHTPB) based fuels hybrid rocket motor. MacCormack decomposition scheme and B-L algebraic turbulence model and two-phase equilibrium flow model were used. The nozzle flow and performance under three oxidizer-to-fuel ratios and four nozzle types were calculated. Effect of oxidizer-to-fuel ratio and nozzle type on nozzle performance was analyzed from the two-phase and gas phase results. Vacuum specific impulse is bound up with oxidizer-to-fuel ratio. This paper will be useful for the hybrid rocket motor design.",

keywords = "HTPB-based fuels, Hybrid rocket motor, NO, Nozzle, Two-phase flow",

author = "Hui Tian and Cai, \{Guo Biao\} and Sun, \{Zai Yong\}",

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journal = "Hangkong Dongli Xuebao/Journal of Aerospace Power",

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T1 - Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor

AU - Tian, Hui

AU - Cai, Guo Biao

AU - Sun, Zai Yong

PY - 2008/6

Y1 - 2008/6

N2 - Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide (N2O)/hydroxyl-terminated polybutadiene CHTPB) based fuels hybrid rocket motor. MacCormack decomposition scheme and B-L algebraic turbulence model and two-phase equilibrium flow model were used. The nozzle flow and performance under three oxidizer-to-fuel ratios and four nozzle types were calculated. Effect of oxidizer-to-fuel ratio and nozzle type on nozzle performance was analyzed from the two-phase and gas phase results. Vacuum specific impulse is bound up with oxidizer-to-fuel ratio. This paper will be useful for the hybrid rocket motor design.

AB - Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide (N2O)/hydroxyl-terminated polybutadiene CHTPB) based fuels hybrid rocket motor. MacCormack decomposition scheme and B-L algebraic turbulence model and two-phase equilibrium flow model were used. The nozzle flow and performance under three oxidizer-to-fuel ratios and four nozzle types were calculated. Effect of oxidizer-to-fuel ratio and nozzle type on nozzle performance was analyzed from the two-phase and gas phase results. Vacuum specific impulse is bound up with oxidizer-to-fuel ratio. This paper will be useful for the hybrid rocket motor design.

KW - HTPB-based fuels

KW - Hybrid rocket motor

KW - NO

KW - Nozzle

KW - Two-phase flow

UR - https://www.scopus.com/pages/publications/46449130876

M3 - 文章

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SN - 1000-8055

VL - 23

SP - 1146

EP - 1150

JO - Hangkong Dongli Xuebao/Journal of Aerospace Power

JF - Hangkong Dongli Xuebao/Journal of Aerospace Power

IS - 6

ER -

Computation of nozzle two-phase flow in a N₂O/HTPB hybrid rocket motor

Abstract

Keywords

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