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An efficient procedure for cascade aeroelastic stability determination using nonlinear, time-marching aerodynamic solversA numerical eigenvalue problem formulation and a practical calculation procedure for exact eigenvalues and corresponding eigenvectors are developed and applied to a nonlinear, two-dimensional, time-marching full potential solver for cascade aeroelastic stability analysis. This procedure is based on the Lanczos recursive method and it directly calculates stability information about a nonlinear steady state. It is compared to conventional approaches in the frequency and time domains developed earlier and is found to be 100-10.000 times more computationally efficient. Eigenvalue constellations and the flutter results for flow through a cascade SR5 propfan airfoil are presented.
Document ID
19930050162
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mahajan, Aparajit J.
(NASA Lewis Research Center Cleveland, OH, United States)
Bakhle, Milind A.
(Toledo Univ.; NASA, Lewis Research Center Cleveland, OH, United States)
Dowell, Earl H.
(Duke Univ. Durham, NC, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 5 (A93-33876 1
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-1631
Report Number: AIAA PAPER 93-1631
Accession Number
93A34159
Funding Number(s)
CONTRACT_GRANT: NAG3-1234
CONTRACT_GRANT: NAG3-1068
CONTRACT_GRANT: NAG3-724
Distribution Limits
Public
Copyright
Other

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