Static and Dynamic on a NACA 0012 Airfoil in the Ames High Reynolds Number Facility on a NACA 0012 Reynolds Number Facility

Abstract

An experimental stud)' has been conducted of the supercritical flows at high subsonic speeds over a NACA 0012 airfoil in order to acquire aerodynamic data suitable l'or evaluating numerical-flow codes. The measurements consisted primarily of static and dynamic pressures on the airfoil and test-channel walls. Shadowgraphs were also taken 'd"the flow field near the airfoil. The tests were performed at free-stream Maeh numbers from approximately O.7 to 0.8, at angles of attack sufficient to include the onset of buffet, and at Reynolds numbers (based on airfoil chord) from 1 million to 14 million. A unique test section was employed which was designed specifically to obtain two-dimensional airfoil data with a minimum of wall interference effects. Boundar)'-layer suction panels were used to minimize sidewall interference effects. Flexible upper and lower walls allowed test-channel area-ruling to nullify Mach number changes induced by the mass removal, to correct fi_r longitudinal boundary-layer growth, and to provide contouring compatible with the streamlines of the model in free air