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Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of Four NACA 6-series Airfoil Sections at Angles of Attack from -2 to 31 Degrees

Homer B. Wilson

出版	National Advisory Committee for Aeronautics, 1953
URL	http://books.google.com.hk/books?id=afP4ZwEACAAJ&hl=&source=gbs_api

註釋

A two-dimensional investigation of the NACA 64-006, 64-008, 64-010, and 64(1)-012 airfoil sections has been made in the Langley low-turbulence pressure tunnel at angles of attack of -2 to 31 degrees and Mach numbers of 0.3 to that for tunnel choke. Measurements were made of the lift, drag, and pitching-moment coefficients for the airfoil models in the smooth condition and with leading-edge roughness. One airfoil model, the NACA 64(1)-012, was also tested with a roughness strip at the 20-percen-chord station.