Abstract
A frequency-domain linearized Euler solver is employed to perform aeroelastic analysis for predicting the control surface buzz onset condition. The predictive capability of the linearized Euler solver for control surface buzz is verified by comparing the predicted onset buzz Mach numbers with wind tunnel data of the National Aerospace Plane flutter model. Using a generic fighter wing as the test bed, a parametric study is performed to investigate the impact of aerodynamic and structural parameters on control surface buzz. These parameters include angle of attack, hinge line sweep angle, airfoil camber, hinge stiffness, and control surface mass. The results of this parametric study suggest that the empirical buzz avoidance criterion used by aerospace industry to avert the buzz problem is oversimplified and should be revised.
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