Exercises

Consider the low-speed airflow over the NACA 0012 airfoil at low angles of attack. The
Reynolds number based on the chord is Rec = 2.88 × 10^6. This flow can reasonably be
modeled as incompressible and inviscid.

1. Coefficient of Pressure

Run a simulation for the NACA 0012 airfoil at angles of attack at 0 degrees and 10 degrees. Plot the pressure coefficient obtained from FLUENT on the same plot as data obtained from experiment The experimental data is from Gregory & O'Reilly, NASA R&M 3726, Jan 1970 and is provided here Follow the aeronautical convention of flipping the vertical axis so that negative Cp values are above and positive Cp values are below. This can be done in MATLAB using set(gca, 'YDir', 'reverse');