Open AccessDesign and Predictions for High-Altitude (Low Reynolds Number) Aerodynamic Flight Experiment
Author(s) -
Donald Greer,
Phil Hamory,
Keith Krake,
Mark Drela
Publication year - 2000
Publication title -
journal of aircraft
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.64
H-Index - 94
eISSN - 1533-3868
pISSN - 0021-8669
DOI - 10.2514/2.2652
Subject(s) - airfoil , mach number , aerospace engineering , aerodynamics , reynolds number , lift to drag ratio , angle of attack , physics , mechanics , aerodynamic center , boundary layer , stall (fluid mechanics) , lift (data mining) , drag divergence mach number , relative wind , lift coefficient , pitching moment , transonic , engineering , computer science , turbulence , data mining
Donald Greer* and Phil Hamory *NASA Dryden Flight Research Center, Edwards, California 93523Keith Krake )Sparta, Inc., Edwards, California 93523andMark Drela !Massachusetts Institute of Technology, Cambridge, Massachusetts 02139A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experi-ment. The experiment will measure the performance parameters of an airfoil at high altitudes (70,000-100,000 It),low Reynolds numbers (2 × los-7 × 10s), and high subsonic Mach numbers (0.5 and 0.65). The airfoil section liftand 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-filmstrip. The details of the planned flight experiment are presented as well as several predictions of the airfoil perfor-
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