4 June 1999 Reduced order modeling for low Reynolds number flow control
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Abstract
This paper presents recent analytical and experimental research to modify and control low Reynolds number flows over prototypical airfoils associated with micro-air-vehicles. The simplified experimental test geometry consists of a meso-scale piezoceramic actuated flap that undergoes peak amplitude displacements of 40 microns. The flap actuator array is designed to modify separation and reattachment location on the airfoil. The location of the reattachment on the upper surface of the prototypical airfoil is measured by an array of MEM's shear stress sensors located downstream. The focus of this paper is the discussion of the status and applicability of reduced order modeling techniques for the derivation of active feedback flow control strategies for the prototypical active airfoil. Frequently, reduced order models are derived from a library of component fluid modes which serve as the basis for a low dimensional approximation of the nonlinear Navier Stokes equations. The methodology discussed in this paper differs markedly from these approaches. We derive a technique employing multiresolution and wavelet approximations of nonlinear Volterra series that represent the input-output dynamics of the system. The accuracy of the resultant low- dimensional input-output models is validated on a benchmark nonlinear aeroelastic testbed.
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Andrew J. Kurdila, Andrew J. Kurdila, Bruce F. Carroll, Bruce F. Carroll, Toshi Nishida, Toshi Nishida, M. Sheplak, M. Sheplak, } "Reduced order modeling for low Reynolds number flow control", Proc. SPIE 3667, Smart Structures and Materials 1999: Mathematics and Control in Smart Structures, (4 June 1999); doi: 10.1117/12.350120; https://doi.org/10.1117/12.350120
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