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Computation of Velocity, Pressure and Temperature Distributions near a Stagnation Point in Planar Laminar Viscous Incompressible Flow
Publié en 2008
As gas turbine temperatures and component life requirements continue to rise, it becomes increasingly important to have a good understanding of the operating temperatures of their components.
The objective of this study was to explorate whether a Hiemenz flow approximation based on measured static pressures near an airfoil leading edge can provide a good estimate of the leading edge heat transfer coefficient.
Finite element and finite volume CFD solvers COMSOL® and FLUENT®, respectively, were each used to produce numerical solutions of the same problem and the results compared.
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