Problem Specification

Consider air flowing over NACA 4412 airfoil. The freestream velocity is 50 m/s and the angle of attack is 2°. Assume standard sea-level values for the freestream properties:
Pressure = 101,325 Pa
Density = 1.2250 kg/m3
Temperature = 288.16 K
Kinematic viscosity v = 1.4607e-5 m2/s
We will determine the lift and drag coefficients under these conditions using FLUENT.

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