I am new in CFD, and i am using Numeca Software (Numeca Fine and CFVIew), i am simulating a NACA airfoil.
I want to calculate some aerodynamic coefficients (for example, Cn, Cd, Cm) but I don't know how to do it...can anybody help me?
Good day. I am sorry to see and reply your message late. Well, for external flow, please do activate in your finehexa or fineopen > computational control > Outputs, then define your flow as external with lift direction, drag direction and etc. Once this option activated, a '.wall' file will be saved after your computation and you may look at this file in your computation folder.
I hope this help.
I had already discovered but thanks anyway! :D
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