TY - GEN
T1 - Experimental-based unified unsteady nonlinear aerodynamic modeling for two-dimensional airfoils
AU - Zakaria, Mohamed Y.
AU - Taha, Haithem E.
AU - Hajj, Muhammad R.
AU - Hussein, Ahmed A.
N1 - Publisher Copyright:
© 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2015
Y1 - 2015
N2 - Unsteady force measurements of a plunging airfoil at different frequencies and mean angles of attack are used to construct frequency response models. The obtained frequency response models are then used to determine the linearized flow dynamics around each mean angle of attack, where an optimization-based linear system identification is performed to minimize the error between the predicted and measured frequency responses. Converting these models to state space form and writing the entries of the matrices as polynomials in the mean angle of attack, a global, unified unsteady model is developed. The developed reduced order model, represented in a state space form, is suitable for characterizing the nonlinear dynamical characteristics of the flow and the associated dynamics and control of a flying object.
AB - Unsteady force measurements of a plunging airfoil at different frequencies and mean angles of attack are used to construct frequency response models. The obtained frequency response models are then used to determine the linearized flow dynamics around each mean angle of attack, where an optimization-based linear system identification is performed to minimize the error between the predicted and measured frequency responses. Converting these models to state space form and writing the entries of the matrices as polynomials in the mean angle of attack, a global, unified unsteady model is developed. The developed reduced order model, represented in a state space form, is suitable for characterizing the nonlinear dynamical characteristics of the flow and the associated dynamics and control of a flying object.
UR - http://www.scopus.com/inward/record.url?scp=84980012798&partnerID=8YFLogxK
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U2 - 10.2514/6.2015-3167
DO - 10.2514/6.2015-3167
M3 - Conference contribution
AN - SCOPUS:84980012798
SN - 9781624103636
T3 - 33rd AIAA Applied Aerodynamics Conference
BT - 33rd AIAA Applied Aerodynamics Conference
T2 - 33rd AIAA Applied Aerodynamics Conference, 2015
Y2 - 22 June 2015 through 26 June 2015
ER -