A wind-tunnel investigation of a Douglas advanced-technology airfoil was conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel (0.3-m TCT). The temperature was varied from 227 K (409 R) to 100 K (180 R) at pressures ranging from about 159 kPa (1.57 atm) to about 514 kPa (5.07 atm). Mach number was varied from 0.50 to 0.78. These variables provided a Reynolds number range (based on airfoil chord) from 6.0 to 30.0 x 10 to the 6th power. This investigation was specifically designed to: (1) test a Douglas airfoil from moderately low to flight-equivalent Reynolds numbers, and (2) evaluate sidewall-boundary-layer effects on transonic airfoil performance characteristics by a systematic variation of Mach number, Reynolds number, and sidewall-boundary-layer removal. Data are included which demonstrate the effects of fixing transition, Mach number, Reynolds number, and sidewall-boundary-layer removal on the aerodynamic characteristics of the airfoil. Also included are remarks on model design and model structural integrity.


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    Title :

    High Reynolds Number Tests of a Douglas Dlba 032 Airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel


    Contributors:
    C. B. Johnson (author) / D. A. Dress (author) / A. S. Hill (author) / P. A. Wilcox (author) / M. H. Bui (author)

    Publication date :

    1986


    Size :

    126 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English