2D Naca validation
Hi everybody, im student of Aeromec and i am trying to get Cl and CD of Naca4412 on 2D, and i need to validate my results.
My datas are:
The aerofoil was create in Gambit
Chord length 1m
Cross section area 0.127876m^2
Viscous model k-epsilon
Re number 6*10^6 (so the velocity inlet to compute from is 87.644m/s??)
On Reference values:
Area: is the cross section area?
Depth: the same as area?
For example, I know that for Re 6*10^6 and 0 AOA the value of Lift is 0.4 but i dont get that one.
Could anyone help me please if i am doing correctly??, im quite new using this software.
what inlet condition did you use (velocity inlet, far field)
Have you done the tutorial of fluent about the wing ni 2D ?? if not, it will a lot ...
Yes, I use velocity inlet as inlet condition. The data's that I put are ok?? (like vel.inlet, area, depth)??
Yes I tried with the tutorial but is inviscid on viscous model.
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