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Thank you, you truly saved me, i was doing it all manually
The legend says that the video's cut like this cause his computer gave out while trying to calculate 28 data points
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???
I have tried this method for an NACA 2415 and i get incorrect totaly incorect coefficient of lift/drag readings ?
just go to the report definitions in the fluent and use the lift/drag as output parameter
Did you validate your results ?
What is the 0.5 in lift coefficient formula and 0.4 in drag coefficient formula????
They are in the definition of the lift and drag coefficients. but i guess both should be 0.5
Lift=(1/2)*rho*Velocity^2*Wing Area
Thank you, you truly saved me, i was doing it all manually
The legend says that the video's cut like this cause his computer gave out while trying to calculate 28 data points
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???
I have tried this method for an NACA 2415 and i get incorrect totaly incorect coefficient of lift/drag readings ?
just go to the report definitions in the fluent and use the lift/drag as output parameter
Did you validate your results ?
What is the 0.5 in lift coefficient formula and 0.4 in drag coefficient formula????
They are in the definition of the lift and drag coefficients. but i guess both should be 0.5
Lift=(1/2)*rho*Velocity^2*Wing Area