An experimental study was made for flow over NACA 0012 airfoil profile wing by running low-speed wind tunnel at 200rpm in our low-speed lab. Experiments were made for angle of attacks of 0 + 0.5, 2+ 0.5, 5+ 0.5 and 8+ 0.5 degrees for the same rpm setting. Data was collected and recorded at a certain frequency using the tunnel data acquisition system. You can find the data on canvas under the homework module. a) Calculate free stream velocity using the pitot-static probe and compare with the tunnel measurement which was on the data file. Compare uncertainties for both measurements and comment on it.