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Experimental transonic steady state and unsteady pressure measurements on a supercritical wing during flutter and forced discrete frequency oscillationsPresent flutter analysis methods do not accurately predict the flutter speeds in the transonic flow region for wings with supercritical airfoils. Aerodynamic programs using computational fluid dynamic (CFD) methods are being developed, but these programs need to be verified before they can be used with confidence. A wind tunnel test was performed to obtain all types of data necessary for correlating with CFD programs to validate them for use on high aspect ratio wings. The data include steady state and unsteady aerodynamic measurements on a nominal stiffness wing and a wing four times that stiffness. There is data during forced oscillations and during flutter at several angles of attack, Mach numbers, and tunnel densities.
Document ID
19890009890
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Piette, Douglas S. (Lockheed-Georgia Co. Atlanta., United States)
Cazier, Frank W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1989
Publication Information
Publication: Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 2
Subject Category
Aerodynamics
Accession Number
89N19261
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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