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 for two cases: a mesh with 15000 elements and a mesh with 40000 elements. 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');

2. Lift and Drag Coefficient

Obtain the lift and drag coefficients from the FLUENT results on the two meshes. Compare these with experimental or expected values (present this comparison as
a table). The experimental values for 0 degree angle of attack are: Cl = 0.025; Cd = 0.0069. The experimental values for 10 degree angle of attack are: Cl = 1.2219; Cd = 0.0138.