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Semi-empirical model for prediction of unsteady forces on an airfoil with application to flutterA semi-empirical model is described for predicting unsteady aerodynamic forces on arbitrary airfoils under mildly stalled and unstalled conditions. Aerodynamic forces are modeled using second order ordinary differential equations for lift and moment with airfoil motion as the input. This model is simultaneously integrated with structural dynamics equations to determine flutter characteristics for a two degrees-of-freedom system. Results for a number of cases are presented to demonstrate the suitability of this model to predict flutter. Comparison is made to the flutter characteristics determined by a Navier-Stokes solver and also the classical incompressible potential flow theory.
Document ID
19930047497
Document Type
Reprint (Version printed in journal)
External Source(s)
Authors
Mahajan, A. J. (NASA Lewis Research Center Cleveland, OH, United States)
Kaza, K. R. V. (NASA Lewis Research Center Cleveland, OH, United States)
Dowell, E. H. (Duke Univ. Durham, NC, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: Journal of Fluids and Structures
Volume: 7
Issue: 1
ISSN: 0889-9746
Subject Category
AERODYNAMICS
Funding Number(s)
CONTRACT_GRANT: NAG3-724
Distribution Limits
Public
Copyright
Other