Force tests of the NACA 23012 and 23012-64 airfoils of 24-inch chord were made in the 8-foot high-speed wind tunnel at Mach numbers ranging from 0.10 to 0.75. Supplementary tests of a 5-inch-chord NACA 23012 airfoil were made in the 24-inch high-speed tunnel to obtain pitching-moment data at higher loadings than could be attained with the 8-foot tunnel models. The results, which were corrected as far as possible for tunnel-wall effects, who the variation with Mach number of lift, drag, and pitching-moment coefficients at angles of attack from -4 deg to 6 deg. At positive lifts the NACA 23012-64 airfoil had slightly higher critical speeds than the NACA 23012 airfoil. At the higher angles of attack in the supercritical speed region, large increases in the magnitude of the pitching-moment coefficient occurred.


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    Title :

    High-Speed Wind-Tunnel Tests of the NACA 23012 and 23012-64 Airfoils


    Contributors:

    Publication date :

    1941


    Size :

    16 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English