Design and predictions for a high-altitude (low Reynolds-number) aerodynamic flight experiment | Zendy

Donald Greer | Zendy; Phil Hamory | Zendy; Keith Krake | Zendy; Mark Drela | Zendy

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Design and predictions for a high-altitude (low Reynolds-number) aerodynamic flight experiment

Author(s) -

Donald Greer,

Phil Hamory,

Keith Krake,

Mark Drela

Publication year - 1999

Publication title -

14th applied aerodynamics conference

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1999-3183

Subject(s) - airfoil , aerospace engineering , pitot tube , aerodynamics , angle of attack , mach number , aerodynamic center , lift to drag ratio , reynolds number , stall (fluid mechanics) , lift (data mining) , boundary layer , physics , relative wind , mechanics , meteorology , pitching moment , engineering , computer science , turbulence , flow (mathematics) , data mining

A sailplane is currently being developed at NASA's Dryden Flight Research Center to support a high altitude flight experiment. The purpose of the experiment is to measure the performance characteristics of an airfoil at altitudes between 100,000 and 70,000 feet at Mach numbers between 0.65 and 0.5. The airfoil lift and drag are measured from pilot and static pressures. The location of the separation bubble and vortex shedding are measured from a hot film strip. The details of the flight experiment are presented. A comparison of several estimates of the airfoil performance is also presented. The airfoil, APEX-16, was designed by Drela (MIT) with his MSES code. A two dimensional Navier-Stokes analysis has been performed by Tatineni and Zhong (UCLA) and another at the Dryden Flight Research Center. The role these analysis served to define the experiment is discussed.

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