TY - GEN
T1 - Low-dimensional models for control of leading-edge vortices
T2 - 45th AIAA Aerospace Sciences Meeting 2007
AU - Ahuja, Sunil
AU - Rowley, Clarence Worth
AU - Kevrekidis, Yannis
AU - Wei, Mingjun
AU - Colonius, Tim
AU - Tadmor, Gilead
PY - 2007
Y1 - 2007
N2 - When an airfoil is pitched up rapidly, a dynamic stall vortex forms at the leading edge and produces high transient lift before shedding and stall occur. The aim of this work is to develop low-dimensional models of the dynamics of these leading-edge vortices, which may be used to develop feedback laws to stabilize these vortices using closed-loop control, and maintain high lift. We first perform a numerical study of the two-dimensional incompressible flow past an airfoil at varying angles of attack, finding steady states using a timestepper-based Newton/GMRES scheme, and dominant eigenvectors using ARPACK. These steady states may be either stable or unstable; we develop models linearized about the stable steady states using a method called Balanced Proper Orthogonal Decomposition, an approximation of balanced truncation that is tractable for large systems. The balanced POD models dramatically outperform models using the standard POD/Galerkin procedure, and are used to develop observers that reconstruct the flow state from a single surface pressure measurement.
AB - When an airfoil is pitched up rapidly, a dynamic stall vortex forms at the leading edge and produces high transient lift before shedding and stall occur. The aim of this work is to develop low-dimensional models of the dynamics of these leading-edge vortices, which may be used to develop feedback laws to stabilize these vortices using closed-loop control, and maintain high lift. We first perform a numerical study of the two-dimensional incompressible flow past an airfoil at varying angles of attack, finding steady states using a timestepper-based Newton/GMRES scheme, and dominant eigenvectors using ARPACK. These steady states may be either stable or unstable; we develop models linearized about the stable steady states using a method called Balanced Proper Orthogonal Decomposition, an approximation of balanced truncation that is tractable for large systems. The balanced POD models dramatically outperform models using the standard POD/Galerkin procedure, and are used to develop observers that reconstruct the flow state from a single surface pressure measurement.
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U2 - 10.2514/6.2007-709
DO - 10.2514/6.2007-709
M3 - Conference contribution
AN - SCOPUS:34250873897
SN - 1563478900
SN - 9781563478901
T3 - Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
SP - 8779
EP - 8790
BT - Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
Y2 - 8 January 2007 through 11 January 2007
ER -