Towards a numerical simulation of supersonic mixing & combustion

The design and off-design studies of hypersonic air-breathing engines face many challenges because of the complexity of their internal flows. Mixing and combustion processes in Supersonic-Combustion Ramjet (scramjet) engines involve complicated aerothermochemical features such as interactions be...

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Main Authors:	Kamel, Mohammed, Idres, Moumen, Owis, Farouk, Hashem, Ali
Format:	Book
Language:	English
Published:	LAP Lambert Academic Publishing 2013
Subjects:	TJ Mechanical engineering and machinery
Online Access:	http://irep.iium.edu.my/43916/ http://irep.iium.edu.my/43916/ http://irep.iium.edu.my/43916/1/2013-Towards_a_Numerical_Simulation_of_Supersonic_Mixing-Book.pdf

id	iium-43916
recordtype	eprints
spelling	iium-439162015-07-21T04:17:21Z http://irep.iium.edu.my/43916/ Towards a numerical simulation of supersonic mixing & combustion Kamel, Mohammed Idres, Moumen Owis, Farouk Hashem, Ali TJ Mechanical engineering and machinery The design and off-design studies of hypersonic air-breathing engines face many challenges because of the complexity of their internal flows. Mixing and combustion processes in Supersonic-Combustion Ramjet (scramjet) engines involve complicated aerothermochemical features such as interactions between shock-waves and boundary-layer, shock induced-combustion and recirculation zones. In this study, a numerical solver is developed and validated to be an efficient design tool capable of simulating these complicated flow features of supersonic combustors. The flow is solved based on the Reynolds Averaged Navier-Stocks equations (RANS), beside a chemical kinetics model for the computation the reactions finite rates. Finite-volume scheme is used where the convective fluxes are discretized by Roe’s scheme using MUSCL approach. And, the diffusive fluxes are centrally discretized. Pointimplicit Runge-Kutta method is applied for time integration. For the code validation, several test cases are to monitor the code ability to solve for the different diffusive and turbulent fluxes, and the chemical source term. In addition, the code is validated by resolving the transverse sonic injection into supersonic air flow in case of Helium injection from a flat plate, and the case of Hydrogen injection in single-strut scramjet engine. The effect of this injection technique in mixing and flame-holding is demonstrated. The results show good agreement with the previous numerical and experimental investigations. And, the numerical simulator proves its accuracy and robustness. LAP Lambert Academic Publishing 2013 Book PeerReviewed application/pdf en http://irep.iium.edu.my/43916/1/2013-Towards_a_Numerical_Simulation_of_Supersonic_Mixing-Book.pdf Kamel, Mohammed and Idres, Moumen and Owis, Farouk and Hashem, Ali (2013) Towards a numerical simulation of supersonic mixing & combustion. LAP Lambert Academic Publishing, Saarbrucken. ISBN 9783659387043 https://www.lap-publishing.com/
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TJ Mechanical engineering and machinery
spellingShingle	TJ Mechanical engineering and machinery Kamel, Mohammed Idres, Moumen Owis, Farouk Hashem, Ali Towards a numerical simulation of supersonic mixing & combustion
description	The design and off-design studies of hypersonic air-breathing engines face many challenges because of the complexity of their internal flows. Mixing and combustion processes in Supersonic-Combustion Ramjet (scramjet) engines involve complicated aerothermochemical features such as interactions between shock-waves and boundary-layer, shock induced-combustion and recirculation zones. In this study, a numerical solver is developed and validated to be an efficient design tool capable of simulating these complicated flow features of supersonic combustors. The flow is solved based on the Reynolds Averaged Navier-Stocks equations (RANS), beside a chemical kinetics model for the computation the reactions finite rates. Finite-volume scheme is used where the convective fluxes are discretized by Roe’s scheme using MUSCL approach. And, the diffusive fluxes are centrally discretized. Pointimplicit Runge-Kutta method is applied for time integration. For the code validation, several test cases are to monitor the code ability to solve for the different diffusive and turbulent fluxes, and the chemical source term. In addition, the code is validated by resolving the transverse sonic injection into supersonic air flow in case of Helium injection from a flat plate, and the case of Hydrogen injection in single-strut scramjet engine. The effect of this injection technique in mixing and flame-holding is demonstrated. The results show good agreement with the previous numerical and experimental investigations. And, the numerical simulator proves its accuracy and robustness.
format	Book
author	Kamel, Mohammed Idres, Moumen Owis, Farouk Hashem, Ali
author_facet	Kamel, Mohammed Idres, Moumen Owis, Farouk Hashem, Ali
author_sort	Kamel, Mohammed
title	Towards a numerical simulation of supersonic mixing & combustion
title_short	Towards a numerical simulation of supersonic mixing & combustion
title_full	Towards a numerical simulation of supersonic mixing & combustion
title_fullStr	Towards a numerical simulation of supersonic mixing & combustion
title_full_unstemmed	Towards a numerical simulation of supersonic mixing & combustion
title_sort	towards a numerical simulation of supersonic mixing & combustion
publisher	LAP Lambert Academic Publishing
publishDate	2013
url	http://irep.iium.edu.my/43916/ http://irep.iium.edu.my/43916/ http://irep.iium.edu.my/43916/1/2013-Towards_a_Numerical_Simulation_of_Supersonic_Mixing-Book.pdf
first_indexed	2023-09-18T21:02:29Z
last_indexed	2023-09-18T21:02:29Z
_version_	1777410716161015808

Towards a numerical simulation of supersonic mixing & combustion

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