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Cp over an airfoil using fluent

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Old   July 10, 2010, 08:35
Default Cp over an airfoil using fluent
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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?


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Old   July 13, 2010, 03:13
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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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