ERROR: End AOA in airfoil table too small k 1 i 1 in Fluent 6.3 -- CFD Online Discussion Forums

September 8, 2010, 07:53	ERROR: End AOA in airfoil table too small k 1 i 1 in Fluent 6.3	#1
Asela New Member Asela Kandamby Join Date: Sep 2010 Posts: 1 Rep Power: 0	Hi everyone, 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? Thanks

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