|August 27, 2014, 06:50||
NACA 0012 2D validation
Join Date: Aug 2014
Posts: 15Rep Power: 3
I have no good experience to aerodynamic analysis. I did some assignments in University days but I want to laern more and doing the validation as per given from here http://turbmodels.larc.nasa.gov/naca0012_val.html.
However I first run at angle of 10 deg but I get very small Cl. I think I am doing some mistake in setup or calculation.
I read in books that in 2D, the lift coefficient Cl is per unit span length, so the equation for coefficient of lift is:
cl_2D=Lift per span length/(0.5 * rho * V^2 * C)
In 3D it is
CL_3D=Lift/(0.5 * rho * V^2 * A)
C is chord length, and rho and V are the freestream conditions and A is planform area..
Now, if I do 2D simulation in fluent, How do I calculate cl_2D coefficient in 2D manually using above formula? Is this Cl calculation would tally with the NASA validation data?
Sorry for my poor English, its not my first language
|September 1, 2014, 06:16||
Join Date: Apr 2012
Location: United Kindom
Posts: 475Rep Power: 12
Lift/span in 3D should be equal to Lift produced in 2D simulation in FLUENT and the Cl data should match with results
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