Jet Vane Heat Transfer Modeling.
Rept. for 1 Oct 85-30 Sep 86,
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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A computational and experimental investigation has been undertaken to study the heat transfer characteristics of jet vanes used in thrust vector control systems. A computational model based on the PHOENICS code is being developed to predict the surface distribution of heat transfer coefficient over a jet vane immersed in a high temperature, high speed rocket exhaust. An experimental program is also being developed to verify the computational model. Keywords PHOENICS computer program Numerical integration.
- Fluid Mechanics
- Rocket Engines