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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
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
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
AIAA PAPER 93-1631
Funding Number(s)
CONTRACT_GRANT: NAG3-1234
CONTRACT_GRANT: NAG3-1068
CONTRACT_GRANT: NAG3-724
Distribution Limits
Public
Copyright
Other

Related Records

IDRelationTitle19930049879Analytic PrimaryAIAA/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. Pts. 1-6