ANSYS Fluent NACA 2412 airfoil with Angle of Attack Rotation and Varying Inlet velocity

[@user-rb4rv7ji4q]

Thank you, you truly saved me, i was doing it all manually

[@kevincastro9886]

The legend says that the video's cut like this cause his computer gave out while trying to calculate 28 data points

[@arcki8127]

hi, i am working on a school project but i am unable to open ansys fluent due to the working directory not being found... is there any way i can link with you via socials???

[@Holzmichie]

I have tried this method for an NACA 2415 and i get incorrect totaly incorect coefficient of lift/drag readings ?

[@mohit-qe4xc]

just go to the report definitions in the fluent and use the lift/drag as output parameter

[@kuzgun_TR]

Did you validate your results ?

[@anusharma-xn1ko]

What is the 0.5 in lift coefficient formula and 0.4 in drag coefficient formula????

[@elhassenaliomer2191]

They are in the definition of the lift and drag coefficients. but i guess both should be 0.5

[@hamzadurmaz8572]

Lift=(1/2)*rho*Velocity^2*Wing Area