Hi. I have written my own 3d panel method code in MATLAB. it could calculate correct pressure coefficients of a NACA0012 airfoil at zero AoA, but fails to get correct result at 5 degree of AOA, pressure coefficients seem to diverge near trailing point. I think this may be caused by wrong calculation of source/doublet influence coefficients (problem with arc tangents functions).
I added figures of both results. could anyone help me with this problem?
I guess the problem with the code in the column % Compute influence coefficients. It would be better if u share the snapshot of code
Manigandan Sekar Thanks for your answer. Here I upload a pdf file containing my influence coefficients calculation in MATLAB with description.
Thanks to Mr. James Nathman, I was able to solve the problem. More details of the answer are available here at this link :
https://www.cfd-online.com/Forums/main/218829-3d-panel-method-code.html
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