An investigation was conducted in the Langley 6- by 28-inch transonic tunnel and the 6- by 19-inch transonic tunnel to determine the two-dimensional aerodynamic characteristics of several rotorcraft airfoils at Mach numbers from 0.35 to 0.90. The airfoils differed in thickness, thickness distribution, and camber. The FX69-H-098, the BHC-540, and the NACA 0012 airfoils were investigated in the 6- by 28-inch tunnel at Reynolds numbers (based on chord) from about 4.7 to 9.3 million at the lowest and highest test Mach numbers respectively. The FX69-H-098, the NLR-1, the BHC-540, and the NACA 23012 airfoils were investigated in the 6- by 19-inch tunnel at Reynolds numbers from about 0.9 to 2.2 million at the lowest and highest test Mach numbers respectively. Design coordinates and static pressure orifice locations for 5 airfoil models given in percent airfoil chord; variables include upper surface, lower surface, stations; 10 tables include numeric data.


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    Titel :

    Two-Dimensional Aerodynamic Characteristics of Several Rotorcraft Airfoils at Mach Numbers from 0.35 to 0.90


    Beteiligte:
    K. W. Noonan (Autor:in) / G. J. Bingham (Autor:in)

    Erscheinungsdatum :

    1977


    Format / Umfang :

    52 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch