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Flutter and Forced Response Analyses of Cascades using a Two-Dimensional Linearized Euler SolverFlutter and forced response analyses for a cascade of blades in subsonic and transonic flow is presented. The structural model for each blade is a typical section with bending and torsion degrees of freedom. The unsteady aerodynamic forces due to bending and torsion motions. and due to a vortical gust disturbance are obtained by solving unsteady linearized Euler equations. The unsteady linearized equations are obtained by linearizing the unsteady nonlinear equations about the steady flow. The predicted unsteady aerodynamic forces include the effect of steady aerodynamic loading due to airfoil shape, thickness and angle of attack. The aeroelastic equations are solved in the frequency domain by coupling the un- steady aerodynamic forces to the aeroelastic solver MISER. The present unsteady aerodynamic solver showed good correlation with published results for both flutter and forced response predictions. Further improvements are required to use the unsteady aerodynamic solver in a design cycle.
Document ID
20000024921
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Reddy, T. S. R. (Toledo Univ. OH United States)
Srivastava, R. (Toledo Univ. OH United States)
Mehmed, O. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
November 1, 1999
Subject Category
Structural Mechanics
Report/Patent Number
E-11960
NASA/TM-1999-209633
NAS 1.15:209633
Funding Number(s)
PROJECT: RTOP 523-26-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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