Lift Hysteresis problem in Oscillating Airfoil
I have run a simulation for Alpha(t)=10+2sinwt. I got Cd hysteresis loop as the same as experimental but I got the Opposite loop for Cl. I am getting higher lift during the downstroke but it should be lower than that of upstroke.
Can anybody help me regarding this problem. N.B. Airfoil is NACA0012, M=0.3, Re=0.54 Million. |
Re: Lift Hysteresis problem in Oscillating Airfoil
Hi,
Obviously you need to validate your model. Check mesh, timestep, convergence, physics, etc etc. It all needs to be correct to get an accurate answer. Glenn Horrocks |
fluent
Quote:
Thank you a lot! |
You are posting on the wrong forum. You are looking for the Fluent forum, this is the CFX forum.
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