Computation of Velocity, Pressure and Temperature Distributions near a Stagnation Point in Planar Laminar Viscous Incompressible Flow
E. Kaufman[1], and E. Gutierrez-Miravete[2][1]Pratt and Whitney, East Hartford, CT, USA
[2]Rensselaer at Hartford, Hartford, CT, USA
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.
