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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. Incompressible, Inviscid Model

Explain why the incompressible, inviscid model for this flow should yield lift coefficient values that match well with experiment but will yield a drag coefficient that is always zero.

2. Boundary Value Problem

What is the boundary value problem (BVP) you need to solve to obtain the velocity and pressure distributions for this flow at an angle of attack of 10◦ ? Indicate governing equations, domain and boundary conditions (u = 0 at a certain boundary etc.). For each of the boundary conditions, indicate also the corresponding boundary type that you need to select in FLUENT.

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');

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