Calculation of Unsteady Control Surface Aerodynamics using Reduced-Order Models

This paper presents computation of unsteady aerodynamics in response to oscillation of control surface using fully implicit unstructured-m esh Euler / Navier-Stokes (N-S) solver and reduced-order model (ROM) based on Volterra theory. This solver was applied to the Benchmark Active Control Technology (BACT) wing with dynamically deflected aileron. The Euler and N-S computation results showed qualitative agreement with experiment both in the steady and unsteady pressure coefficients, a lthough there were some small quantitative discrepancies both in the magnitude an d phase angle of pressure coefficient. The Volterra-based ROM approach with the N-S solver was also applied to the BACT wing with harmonically oscillating aileron. The comparison of unsteady pressure coefficients between direct and convolved results showed excellent agreement. It has been shown that the ROM approach resulted in good and rapid prediction of the unsteady aerodynamic responses to the aileron oscillation.

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