I think you're right Dan, I don't think the Viterna model is far off a flat plate assumption anyway.
However, if you were using a NACA 4412, which has a zero-lift angle of attack of about -4 degrees, would you shift the viterna model by 4 degrees to the left?
For some reason I can't get...
Even if the wake makes it invalid, I'd still like to have a way of roughly predicting CL and CD for a full 360 degree sweep incase its ever needed for something else (i've spent all week programming on this so I may as well finish!).
Just realised that Ive never seen the the viterna corrigan...
I read that in the documentation too :(
Suppose I'll just have to use the Viterna post-stall model, although I've never seen it used on a non-symetrical aerofoil. It can't be too dificult surely.
It's for a vertical axis wind turbine simulation.
Hi,
I want to use xfoil to get CL and CD data for all angles of attack, i.e. the full 360 degrees.
This is for a NACA 4412 profile, Re = 0.708*10^6.
Has anyone ever tried this?
I'm beginning to think it's impossible as I get bombarded by "non convergence" and "no stagnation point found"...
