Development of Reduced-Order Models for Aeroelastic Analysis and Flutter Prediction Using the CFL3Dv6.0 Code
نویسندگان
چکیده
A reduced-order model (ROM) is developed for aeroelastic analysis using the CFL3D version 6.0 computational uid dynamics (CFD) code, recently developed at the NASA Langley Research Center. This latest version of the ow solver includes a deforming mesh capability, a modal structural de nition for nonlinear aeroelastic analyses, and a parallelization capability that provides a signi cant increase in computational eÆciency. Flutter results for the AGARD 445.6 Wing computed using CFL3D v6.0 are presented, including discussion of associated computational costs. Modal impulse responses of the unsteady aerodynamic system are then computed using the CFL3Dv6 code and transformed into state-space form. Important numerical issues associated with the computation of the impulse responses are presented. The unsteady aerodynamic state-space ROM is then combined with a state-space model of the structure to create an aeroelastic simulation using the MATLAB/SIMULINK environment. The MATLAB/SIMULINK ROM is used to rapidly compute aeroelastic transients including utter. The ROM shows excellent agreement with the aeroelastic analyses computed using the CFL3Dv6.0 code directly.
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