Publication Date:
2019-07-13
Description:
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.
Keywords:
Aerodynamics
Type:
NASA/TM-1999-206579
,
NAS 1.15:206579
,
H-2340
,
AIAA Paper 99-3183
,
14th Computational Fluid Dynamics; Jun 28, 1999 - Jul 01, 1999; Norfolk, VA; United States|17th Applied Aerodynamics; Jun 28, 1999 - Jul 01, 1999; Norfolk, VA; United States
Format:
application/pdf
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