I was recommended some different tutorials to learn this software, but this was much clearer and concise that the others I was trying to watch. It also uses the updated version of XFLR5. Thank you!
Wow! Thank you very much for such a nice explanation. I have watched several videos but they take so much of our time explaining things not much relevant to me. This was a perfect video. Good job!!
I have a problem related to simulating FX 61128 airfoil using XFLR5. I don't get any results on analysis. The question is can I get results for any random airfoil? Or Is it like a predefined set of airfoils which are used for wing analysis?
hi I am just curious in minute 12.14 where u stated that "viscous effect is not actually calculate here". However there is a viscous function and a display of displacement thickness which through my imagination that is actually a boundary layer.
- With this I mean there are some limitations within xflr5 to calculate viscous effects. That is there is lack of interaction between boundary layer and inviscid flow. Also the estimation of viscous drag. - Potential methods such as VLM and 3d Panel methods merely interpolate 2d viscous drag from local wing lift that is not good. - Their is lack of interactive boundary layer loop, which is a coupling method between potential flow and viscous flow on surfaces. - The effect of the boundary layer is to modify the geometry of surfaces and to disturb the inviscid potential flow. - A loop is therefore needed to reach a solution that satisfies both the viscous model and the potential flow model. - This loop is not implemented in the panel methods available in xflr5. - Consequences / drawbacks are: * The lift is a linear function of the a.o.a., unlike with XFoil or with the non-linear LLT. * Significant differences in the lift coefficient predictions at low Reynolds numbers. * The potential flow model is only valid in conditions of limited flow separation. Hope this helps, thanks.
