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cl,cd data for pitching/plunging airfoil at low Re

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Old   February 3, 2006, 23:22
Default cl,cd data for pitching/plunging airfoil at low Re
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Quarkz
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Does anyone know of reference (numerical/experimental) for cl, cd, cp (lift,drag, pressure coefficient) data for pitching/plunging airfoil at low Re, preferably around 100 - 500?

I need it for comparison against my incompressible NS solver.

Thanks
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Old   August 9, 2011, 03:11
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amir faghihi
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Quote:
Originally Posted by Quarkz
;40297
Does anyone know of reference (numerical/experimental) for cl, cd, cp (lift,drag, pressure coefficient) data for pitching/plunging airfoil at low Re, preferably around 100 - 500?

I need it for comparison against my incompressible NS solver.

Thanks
hi i want too valid my incompressible NS code for pure plunging airfoil. can you find any data for your validation?
Thanks
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