Cd max of airfoil
i am doing my university project on a naca airfoil with same profiled flap. i am using RNG k-epsilon model with standard wall function, in case that Angle of attack 10 degrees and flap deflection 20 degrees .
when i give option to print and plot drag an lift coefficients, i am getting error like read-data: invalid plot file format
i am attaching the mesh file of my problem
can any one help me how to avoid that error and how to find the Cd max and Cl max
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