[reynolds_master]

Hey! I'm asked to compute the pressure coefficient distributions ܿfor the upper and lower surfaces of a NACA0012 airfoil based on the experimental data provided, which is the one I'm attaching in the image. Then, I have to calculate the lift coefficient distributions ܿand the airfoil global lift coefficient. The truth is, I'm absolutely clueless on how to reproduce the Vortex Panel Method in MATLAB or any other software (no java-applets or 3rd party apps are allowed), and that's why I'm asking you guys at least for some advice or if you know how to struct this program in MATLAB code or something similar. I'm not asking for a super-program, just the very basics, as I'm clueless and even don't know how to start. The speed is 15.3 m/s.

The data I have is the measure of the pressure in 20 static ports, decalated from the upper and lower parts of the airfoil, as you can see in the image, the angle of attack, lift, drag, pitching moment and rho. Could you help me? That'd be really appreciated! THANKS VERY MUCH in advance!!!!