Computational Simulation of a Sonic Jet into a Supersonic Cross Flow, Using Parallel Computing

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Sheida, Mojtaba | 2009

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 40197 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Rahni, Taeibi
Abstract:
Today’s Missiles are very maneuverable and to increase this ability, side jets are used. Beneficial usages of such systems are in fast responding and more accuracy in response of forces and moments to change directions. In jet in cross flow interactions, boundary layer is separated in front of the jet creating horseshoe vortices plus compression and expansion waves. In this research, we have developed a CFD code to simulate this flow, using the Spalart-Allmaras turbulence model and parallel computing. Then, we have studied the influence of free stream Mach number and momentum ratio. In this simulation, 2 million nodes were used in the computational domain. Also parallel processing with shared memory structure, domain decomposition method, and dynamic load balancing were used. The results indicate considerable effects of bow shock on the jet penetration and also on the flow region upstream and downstream of the jet. Also, the speed-up obtained is considerably close to the ideal one
Keywords:
Parallelization ; Domain Decomposition ; Spalart-Almaras Turbulence Model ; Sonic Jet in Super Sonic Cross Flow

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