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Flow over an Airfoil

Created using ANSYS 14.0

Problem Specification

In this tutorial, we will show you how to simulate a NACA 0012 Airfoil at a 6 degree angle of attack placed in a wind tunnel.

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A NACA 0012 Airfoil is placed in a wind tunnel with the following free stream conditions:

Reynolds Number : 2.88e6
x velocity: 1 m/s
viscosity: 3.4722e-7 kg/m*s

Using FLUENT, we will create a simulation of this experiment. Afterwards, we will compare values from the simulation and data collected from experiment.

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Go to Step 1 - : Pre-Analysis & Start-Up

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