ERROR: End AOA in airfoil table too small k 1 i 1 in Fluent 6.3
i am using fluent 6.3 and i'm trying in generating results for a 2 bladed helicopter having 2 sections. I have the sectional lift and drag arranged in the .dat files which is similar to the standara format used in the NACA 0015.
My AOA varies from -20 to 26 degrees.
When i run it on Fluent i seem to get this error no matter how much i change the format.
Does anyone have a idea on the matter?
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