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SIMULATION: ANSYS WB - Airfoil - panel
SIMULATION: ANSYS WB - Airfoil - panel
Note

Under Construction

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.

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