...
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.
...
...
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.
...