[al3x]

Hello everyone,

I would really appreciate any help to complete my script implementing a linear-strength vortex method as described by Katz and Plotkin in Low Speed Aerodynamics (Section 11.4.2 and Program no.7 in Appendix). This is my first script implementing a panel method and I have faced some (not only)programming difficulties.

So, I was trying to get a Cp plot of an airfoil but I always received a random fuzzy line (just garbage). It's been 3 days now that I'm trying to correct this and still no luck. BUT, in my surprise, I gave as input just the upper surface of the airfoil and I received the true Cp plot and the same for the lower. That being said, I can compute the two airfoil surfaces alone but if I input the full airfoil.dat file I get garbage.

Are the upper and lower vortex-sheets independent? The collocate points of the lower vortex-sheet should not be affected by the vortices of the upper vortex-sheet (and vice-versa)? It was my idea that the airfoil works as one vortex-sheet alone.. do I have to separate them?

Thanks in advance!


The links below correspond to the photos of the Cp plots with the two surfaces alone (correct) and the airfoil (fuzzy line - garbage):

Upper Surface Cp & Airfoil (S1210)
https://drive.google.com/open?id=0B8...0V4TlViYkNGT3c

Lower Surface Cp & Airfoil
https://drive.google.com/open?id=0B8...XQzZV8zbmkzV28

Airfoil Cp
https://drive.google.com/open?id=0B8...FVnZTNBNGRqSG8