NDLI: Experimental transonic steady state and unsteady pressure measurements on a supercritical wing during flutter and forced discrete frequency oscillations

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Experimental transonic steady state and unsteady pressure measurements on a supercritical wing during flutter and forced discrete frequency oscillations

Content Provider	NASA Technical Reports Server (NTRS)
Author	Piette, Douglas S. Cazier Jr., Frank W.
Copyright Year	1989
Description	Present 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.
File Size	3624629
Page Count	28
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19890009890
Archival Resource Key	ark:/13960/t74v1hc03
Language	English
Publisher Date	1989-02-01
Access Restriction	Open
Subject Keyword	Aerodynamics Transonic Flow Computational Fluid Dynamics Unsteady Flow Steady State Computer Programs Airfoil Oscillations Airfoil Profiles Unsteady Aerodynamics Wind Tunnel Tests Supercritical Wings Stiffness Flutter Analysis Pressure Measurement Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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