The legend says that the video's cut like this cause his computer gave out while trying to calculate 28 data points
Thank you, you truly saved me, i was doing it all manually
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 ?
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???
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
The legend says that the video's cut like this cause his computer gave out while trying to calculate 28 data points
Thank you, you truly saved me, i was doing it all manually
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 ?
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???
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