Vortex Panel Method: Normal Velocity Geometric Integral [K(ij)]

[@ryu66677]

wow.. amazing! greeting from korea. thank you.

[@casper6349]

Hi Josh, thanks for the upload. I have a question regarding the application of this method to thin airfoil theory. In the case of modelling a non-cambered airfoil according to thin airfoil theory, the vortex sheet becomes a straight horizontal line. This means phi = 0 and y_i = Y_j for every panel. Therefore, E = 0 for every K_i_j in the computation of the integral in 14:34. Do you have any way of working around this? Or is this method simply not applicable to thin, non-cambered airfoils.

[@RainTurtlez]

i have the same concern. did you fix this?

[@casper6349]

@@RainTurtlez Yes I fixed it. I used a model described by Katz and Allen in their book "Low Speed Aerodynamics". I believe the model is mentioned in Chapter 11 of the book. The model is called "the lumped vortex element method".

[@Aerok-t1r]

Hi, Josh. Can you check my e mail I just sent you.