Mathematical Modeling of Reactive Fluid Flow in Solid Rocket Motor Combustion Chamber with/without Nozzle
Hegab, A., Wilson, S., Elaskary, W., El-Behery, S., Yousif, K. (2011). Mathematical Modeling of Reactive Fluid Flow in Solid Rocket Motor Combustion Chamber with/without Nozzle. EKB Journal Management System, 14(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011), 1-24. doi: 10.21608/asat.2011.23266
A. M. Hegab; S. A. Wilson; W. A. Elaskary; S. M. El-Behery; K. A. Yousif. "Mathematical Modeling of Reactive Fluid Flow in Solid Rocket Motor Combustion Chamber with/without Nozzle". EKB Journal Management System, 14, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011, 2011, 1-24. doi: 10.21608/asat.2011.23266
Hegab, A., Wilson, S., Elaskary, W., El-Behery, S., Yousif, K. (2011). 'Mathematical Modeling of Reactive Fluid Flow in Solid Rocket Motor Combustion Chamber with/without Nozzle', EKB Journal Management System, 14(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011), pp. 1-24. doi: 10.21608/asat.2011.23266
Hegab, A., Wilson, S., Elaskary, W., El-Behery, S., Yousif, K. Mathematical Modeling of Reactive Fluid Flow in Solid Rocket Motor Combustion Chamber with/without Nozzle. EKB Journal Management System, 2011; 14(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011): 1-24. doi: 10.21608/asat.2011.23266

Mathematical Modeling of Reactive Fluid Flow in Solid Rocket Motor Combustion Chamber with/without Nozzle

International Conference on Aerospace Sciences and Aviation Technology
Article 43, Volume 14, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011, May 2011, Page 1-24  XML PDF (2.19 MB)
Document Type: Original Article
DOI: 10.21608/asat.2011.23266
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Authors
A. M. Hegab1, 2; S. A. Wilson2; W. A. Elaskary2; S. M. El-Behery2; K. A. Yousif2
1Professor, corresponding author+
2Mechanical Power Engineering Department, Faculty of Engineering, Menoufiya University, Shebin El-Kom, EGYPT.
Abstract
In the present work, a complete simulation of reactive flow in the combustion chamber of a rocket motor equipped with convergent-divergent nozzle has been introduced. The model describes the combustion process inside the combustion chamber considering a steady premixed reactant gas injected through side porous walls of the combustion chamber.
The products flow through a convergent-divergent nozzle with adiabatic impermeable walls. The reactants are treated as two-dimensional, multi-components, turbulent compressible flow. The local properties of the mixture are calculated and updated during the solution process. At the boundary of the combustion chamber, a constant mass flux and predefined properties are considered. The proposed model employs the basic conservation equations of continuity, momentum and energy as well as the finite rate of reaction and species transport equations. Finite volume method is used to solve the basic nonlinear partial differential equations numerically. The details of the numerical scheme, structure of the used grids, numerical accuracy and stability are introduced. The effect of grid resolution as well as the validity of the results is included. The results showed fair agreement with other models in the literature; specially the reaction zone depth, temperature contours and species concentration along the entire space of the combustion chamber.
Keywords
Solid propellant; sandwich propellant; Diffusion and Premixed Flames; Convergent and Divergent Nozzle; Reactive Flow in Rockets
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