NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
NACA 0012 benchmark model experimental flutter results with unsteady pressure distributionsThe Structural Dynamics Division at NASA Langley Research Center has started a wind tunnel activity referred to as the Benchmark Models Program. The primary objective of the program is to acquire measured dynamic instability and corresponding pressure data that will be useful for developing and evaluating aeroelastic type CFD codes currently in use or under development. The program is a multi-year activity that will involve testing of several different models to investigate various aeroelastic phenomena. This paper describes results obtained from a second wind tunnel test of the first model in the Benchmark Models Program. This first model consisted of a rigid semispan wing having a rectangular planform and a NACA 0012 airfoil shape which was mounted on a flexible two degree-of-freedom mount system. Experimental flutter boundaries and corresponding unsteady pressure distribution data acquired over two model chords located at the 60 and 95 percent span stations are presented.
Document ID
19920051845
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rivera, Jose A., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Dansberry, Bryan E.
(NASA Langley Research Center Hampton, VA, United States)
Bennett, Robert M.
(NASA Langley Research Center Hampton, VA, United States)
Durham, Michael H.
(NASA Langley Research Center Hampton, VA, United States)
Silva, Walter A.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-2396
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Location: Dallas, TX
Country: United States
Start Date: April 13, 1992
End Date: April 15, 1992
Accession Number
92A34469
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available