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Design and Predictions for a High-Altitude (Low-Reynolds-Number) Aerodynamic Flight ExperimentA 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.
Document ID
19990049398
Acquisition Source
Armstrong Flight Research Center
Document Type
Reprint (Version printed in journal)
Authors
Greer, Donald
(NASA Dryden Flight Research Center Edwards, CA United States)
Hamory, Phil
(NASA Dryden Flight Research Center Edwards, CA United States)
Krake, Keith
(Sparta, Inc. Edwards AFB, CA United States)
Drela, Mark
(Massachusetts Inst. of Tech. Cambridge, MA United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1999
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-1999-206579
AIAA Paper 99-3183
H-2340
NAS 1.15:206579
Meeting Information
Meeting: 14th Computational Fluid Dynamics
Location: Norfolk, VA
Country: United States
Start Date: June 28, 1999
End Date: July 1, 1999
Funding Number(s)
PROJECT: RTOP 529-10-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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