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Calculation of transonic aileron buzzAn implicit finite-difference computer code that uses a two-layer algebraic eddy viscosity model and exact geometric specification of the airfoil has been used to simulate transonic aileron buzz. The calculated results, which were performed on both the Illiac IV parallel computer processor and the Control Data 7600 computer, are in essential agreement with the original expository wind-tunnel data taken in the Ames 16-Foot Wind Tunnel just after World War II. These results and a description of the pertinent numerical techniques are included.
Document ID
19790035540
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Steger, J. L. (NASA Ames Research Center Moffett Field, CA, United States)
Bailey, H. E. (NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 79-0134
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: New Orleans, LA
Start Date: January 15, 1979
End Date: January 17, 1979
Sponsors: Astronautics, American Institute of Aeronautics
Accession Number
79A19553
Distribution Limits
Public
Copyright
Other

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