Question: Question 3 (Vortex Panel Analysis) - 10 marks a) Use the provided vortex panel code to simulate flow over a NACA 0012 airfoil (http://

Question 3 (Vortex Panel Analysis) - 10 marks a) Use the provided vortex panel code to simulate flow over a NACA 0012 airfoil (http:// airfoiltools.com/airfoil/naca4digit - be sure to specify closed trailing edge) using 20, 40, 80, and 160 panels around the airfoil at a = 0 degrees. Create a single plot combining the results for each number of panels. Comment on the behaviour of the Cp curve as you increase the number of panels. How do these results compare with your source panel results from assignment 3? Page 2 of 3 b) Using 160 panels, create plots of Cp vs x/c at angles of attack = 0, 5, 10, and 15 degrees. In each plot include the experimental pressure coefficient data of Gregory and O'Reilly found near the bottom here: https://turbmodels.larc.nasa.gov/naca0012_val.html (NOTE: There is no experimental data for 5 degrees). Using 160 panels, create a plot of C vs for the angles of attack used in the experimental data of Ladson in the "80 grit experiment (same link as in part b). Plot the experimental data alongside the results obtained using the vortex panel code. Comment on the level of agreement and discuss the cause of any differences you may observe

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