02 February 2016 7 6K Report

I follow properly the guide of Cornell University, but I still get far different from the University. My lift coefficient = 1.9e-3 and drag coefficient= 1.9e-2. I tried to figure out it but I still don't find out the reason. Any suggestion, please help me. Thanks!

https://confluence.cornell.edu/display/SIMULATION/FLUENT+-+Flow+over+an+Airfoil

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