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Static and dynamic pressure measurements on a NACA 0012 airfoil in the Ames High Reynolds Number FacilityThe supercritical flows at high subsonic speeds over a NACA 0012 airfoil were studied to acquire aerodynamic data suitable for evaluating numerical-flow codes. The measurements consisted primarily of static and dynamic pressures on the airfoil and test-channel walls. Shadowgraphs were also taken of the flow field near the airfoil. The tests were performed at free-stream Mach numbers from approximately 0.7 to 0.8, at angles of attack sufficient to include the onset of buffet, and at Reynolds numbers from 1 million to 14 million. A test action was designed specifically to obtain two-dimensional airfoil data with a minimum of wall interference effects. Boundary-layer suction panels were used to minimize sidewall interference effects. Flexible upper and lower walls allow test-channel area-ruling to nullify Mach number changes induced by the mass removal, to correct for longitudinal boundary-layer growth, and to provide contouring compatible with the streamlines of the model in free air.
Document ID
19850019511
Document Type
Technical Publication (TP)
Authors
Mcdevitt, J. B. (NASA Ames Research Center Moffett Field, CA, United States)
Okuno, A. F. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1985
Subject Category
AERODYNAMICS
Report/Patent Number
A-85100
NAS 1.60:2485
NASA-TP-2485
Funding Number(s)
PROJECT: RTOP 505-31-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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