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Airfoil stall penetration at constant pitch rate and high Reynolds numberThe model wing consists of a set of fiberglass panels mounted on a steel spar that spans the 8 ft test section of the UTRC Large Subsonic Wind Tunnel. The first use of this system was to measure surface pressures and flow conditions for a series of constant pitch rate ramps and sinusoidal oscillations a Mach number range, a Reynolds number range, and a pitch angle range. It is concluded that an increased pitch rate causes stall events to be delayed, strengthening of the stall vortex, increase in vortex propagation, and increase in unsteady airloads. The Mach number range causes a supersonic zone near the leading edge, stall vortex to be weaker, and a reduction of unsteady airloads.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Lorber, Peter F.
(United Technologies Research Center East Hartford, CT, United States)
Carta, Franklin O.
(United Technologies Research Center East Hartford, CT, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1989
Publication Information
Publication: NASA, Langley Research Center, Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 2
Subject Category
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.
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