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A High Altitude-Low Reynolds Number Aerodynamic Flight ExperimentA 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.
Document ID
20000108875
Acquisition Source
Armstrong Flight Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Greer, Don
(NASA Dryden Flight Research Center Edwards, CA United States)
Krake, Keith
(NASA Dryden Flight Research Center Edwards, CA United States)
Hamory, Phil
(NASA Dryden Flight Research Center Edwards, CA United States)
Drela, Mark
(Massachusetts Inst. of Tech. MA United States)
Lee, Seunghee
Date Acquired
August 19, 2013
Publication Date
January 1, 1999
Subject Category
Aerodynamics
Meeting Information
Meeting: Applied Aerodynamics
Location: Norfolk, VA
Country: United States
Start Date: June 28, 1999
End Date: July 1, 1999
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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