The tabulated data from tests of a six inch chord NPL 9510 airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel. The tests were performed over the following range of conditions: Mach numbers of 0.35 to 0.82, total temperature of 94 K to 300 K, total pressure of 1.20 to 5.81 atm, Reynolds number based on chord of 1.34 x 10 to the 6th to 48.23 x 10 to the 6th, and angle of attack of 0 deg to 6 deg. The NPL 9510 airfoil was observed to have decreasing drag coefficient up to the highest test Reynolds number.


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    Titel :

    Tabulation of Data from Tests of an Npl 9510 Airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel


    Beteiligte:
    R. V. Jenkins (Autor:in)

    Erscheinungsdatum :

    1983


    Format / Umfang :

    237 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch