A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experiment. The experiment will measure the performance parameters of an airfoil at high altitudes (70,000 to 100,000 ft), low Reynolds numbers (200,000 to 700,000), and high subsonic Mach numbers (0.5 and 0.65). The airfoil section lift and drag are determined from pitot 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. Several predictions of the airfoil performance are also presented. Mark Drela from the Massachusetts Institute of Technology designed the APEX-16 airfoil, using the MSES code. Two-dimensional Navier-Stokes analyses were performed by Mahidhar Tatineni and Xiaolin Zhong from the University of California, Los Angeles, and by the authors at NASA Dryden.


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    Title :

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


    Contributors:
    Greer, Donald (author) / Hamory, Phil (author) / Krake, Keith (author) / Drela, Mark (author)

    Conference:

    14th Computational Fluid Dynamics ; 1999 ; Norfolk, VA, United States
    17th Applied Aerodynamics ; 1999 ; Norfolk, VA, United States


    Publication date :

    1999-07-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :