|July 10, 2010, 08:35||
Cp over an airfoil using fluent
Join Date: Aug 2009
Posts: 9Rep Power: 8
How to calculate/determine the Cp at upper and lower surface of an airfoil at user-defined points (at upper and lower surface), instead of cslculating Cp at each grid point (cell/node).
I have experimental data at some certain locations, I want to compare at those locations.
How can I do this either by using Fluent or tecplot?
|July 13, 2010, 03:13||
Join Date: May 2009
Posts: 90Rep Power: 8
maybe you can define upper and lower surface as different walls.
than you can plot Cp for both surfaces and you can compare with experimental data.
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