Comparative Studies on Various Turbulent Models with Liquid Rocket Nozzle through Computational Tool

Abstract:

Supersonic flows associated with missiles, aircraft, missile engine intake and rocket nozzles are often steady. In this present work, the computational analysis was conducted on C-D (convergent –divergent) nozzle for understanding the flow regime with various flow properties such as velocity and various turbulent models (spalert almaras, K-ε and K-ω). The Scale down model of C-D nozzle was chosen for this study and it was modelled computationally with Gambit software package. In this integrated component model, the inlet flow is assumed a two-dimensional, steady, compressible, turbulent and supersonic. The physics based mathematical model of the considered flow consists of conservation of mass, momentum and energy equations subject to appropriate boundary conditions as defined by the physical problem stated above. The system of the governing equations with turbulent effects is solved numerically using different turbulence models to demonstrate their numerical accuracy in predicting the characteristics of turbulent gas flow in such complex geometry. Fluent software package was used for solving gas flow equations with turbulence models. The Mach number was chosen for different cases of analyses were 1.2, 1.5 and 2. For each case, different turbulence were engaged and solved and all the results were compared finally.

• Periodical: Advanced Materials Research (Volumes 984-985)
• Pages: 1204-1209
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.984-985.1204
• Online since: July 2014
• Authors: N.K. Mohamad Tanveer, Chandran Mohanraj*, K. Jegadeesan, S. Maruthupandiyan
• Keywords: Computational Fluid Dynamics (CFD), Supersonic Flow, Turbulence Model

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