For this project, you have to show Transonic Airfoil analysis over a range in Mach numbers to see the effect on lift and drag coefficients.
Follow the tutorial, but set the far-field freestream conditions to sea level standard pressure and temperature. Then run the solution for Mach numbers at 0.5, 0.6 and 0.7, and then from 0.72 through 0.84 in increments of no more than 0.04. Record the lift and drag coefficients for each case to plot versus Mach number.
After each solution, plot a contour plot of Mach number over your airfoil and save it. You can save images of the graphics window by using the "Save Pictures" button next to the file save icon in the upper left part of the window. Also, create an xy plot of Skin Friction Coefficient (under Wall Fluxes) to see if separation occurs (a negative shear stress) after the shock wave on the surface. Save this plot for inclusion in your report.
Create a project report showing your lift and drag versus Mach number plots along with the Mach contour plots and surface shear stress plots.