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Showing 1 to 1 of 1 for “"Boundary Layer Separations"”.
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Experimental Investigation of Transonic Shock Oscillations on NACA 0018 at Incidence
A NACA 0018 airfoil model with a 3-inch chord was mounted into the trisonic wind tunnel at the National Center for Physical Acoustics at the University of Mississippi. Tunnel runs were conducted with the angle of incidence increasing from 0 degrees to 6 degrees at 1 degree increments, while the …