This report presents in graphic and tabular forms the aerodynamic coefficient and surface pressure distribution data for a NASA SC(2)-0714 airfoil tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel. The test was another in a series of tests involved in the joint NASA/U.S. Industry Advanced Technology Airfoil Tests program. This 14% thick supercritical airfoil was tested at Mach numbers from 0.6 to 0.76 and angles of attack from -2.0 to 6.0 degrees. The test Reynolds numbers were 4 million, 6 million, 10 million, 15 million, 30 million, 40 million, and 45 million.


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    Title :

    Aerodynamic Performance and Pressure Distributions for a NASA (National Aeronautics and Space Administration) SC(2)-0714 Airfoil Tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel


    Contributors:
    R. V. Jenkins (author) / A. S. Hill (author) / E. J. Ray (author)

    Publication date :

    1988


    Size :

    300 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English