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Old   August 12, 2015, 07:01
Default Lifting Surface Model
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Hey Guys,

I am trying Vortex lattice method using Vortex rings of a NACA0012 rectangular wing and I am getting the profile for both circulation and wake.

But when I change the number of panels, the profile shape is same but the values are changing. That is, if I increase the panel count, the peak circulation/wake vortex strength is decreasing by 30-40%.

Could you please tell me why there is a change in value with panel density and Is there any fix for this [at least, to minimise the change] ??

Also, This model does not include thickness effect and is there any solution to include it as well ??? A good tutorial will be helpful.

Thanks in advance !!!
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Old   August 12, 2015, 17:30
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I don't know the details, but it appears to me that what you're experiencing is nothing more than the effect of grid resolution. Just as with any other numerical method, as you increase the grid resolution (the number of vortex lattices in your case) the solution should (hopefully) converge. You might have had a very low resolution the first time around. Try using even more lattices and check the trend of your peak circulation, etc. Just keep in mind that the vortex lattice method is low-order, so it may require higher-than-normal resolution for the solution to converge.

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aerodynamic, lifting surface model, panel method, vortex lattice

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