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Author: Rajesh Bhaskaran, Cornell University

{color:#ff0000}{*}Problem Specification{*}{color}
[1. Create Geometry in GAMBIT|FLUENT - Flow over an Airfoil- Step 1] 
[2. Mesh Geometry in GAMBIT|FLUENT - Flow over an Airfoil- Step 2] 
[3. Specify Boundary Types in GAMBIT|FLUENT - Flow over an Airfoil- Step 3] 
[4. Set Up Problem in FLUENT|FLUENT - Flow over an Airfoil- Step 4] 
[5. Solve\!|FLUENT - Flow over an Airfoil- Step 5] 
[6. Analyze Results|FLUENT - Flow over an Airfoil- Step 6] 
[7. Refine Mesh|FLUENT - Flow over an Airfoil- Step 7] 
[Problem 1|FLUENT - Flow over an Airfoil- Problem 1] 
[Problem 2|FLUENT - Flow over an Airfoil- Problem 2]
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h2. Problem Specification


!airfoil.jpg!

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:
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Pressure = 101,325 Pa
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Density = 1.2250 kg/m3
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Temperature = 288.16 K
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Kinematic viscosity _v_ = 1.4607e-5 m2/s
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We will determine the lift and drag coefficients under these conditions using  FLUENT.
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Go to [Step 1: Create Geometry in GAMBIT|FLUENT - Flow over an Airfoil- Step 1]

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