A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experiment. The experiment will measure the performance parameters or an airfoil at high altitudes (70,000 - 100,000 ft), low Reynolds numbers (2 x 10(exp 5) - 7 x 10(exp 5)), and high subsonic Mach numbers (0.5 and 0.65). The airfoil section lift and drag are determined from pilot and static pressure measurements. The locations of the separation bubble, Tollmien-Schlichting boundary-layer instability frequencies, and vortex shedding are measured from a hot-film strip. The details of the planned flight experiment are presented as well as several predictions of the airfoil performance.


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    Title :

    Design and Predictions for High-Altitude (Low Reynolds Number) Aerodynamic Flight Experiment


    Contributors:
    D. Greer (author) / P. Harmory (author) / K. Krake (author) / M. Drela (author)

    Publication date :

    2000


    Size :

    6 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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