Heat Transfer Modelling of Thrust Vector Control Systems
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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This thesis presents a model of heat transfer phenomenon in thrust vector control systems, using the PHOENICS computer code. To simplify the problem of heat transfer to solid objects in rocket exhaust, simple wedge bodies have been examined in supersonic gas flow for both turbulent and laminar flow cases. The study gives an estimate of skin friction coefficient, surface heat flux, heat transfer coefficient, Stanton number distributions, and computer run times.
- Fluid Mechanics
- Combustion and Ignition