Computation of Velocity, Pressure and Temperature Distributions near a Stagnation Point in Planar Laminar Viscous Incompressible FlowE. Kaufman, and E. Gutierrez-Miravete
Pratt and Whitney, East Hartford, CT, USA
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.