Predicting wing-pylon-nacelle configuration flutter characteristics using adaptive continuation method

Abstract In this study, the aeroelastic response of a wing-pylon-nacelle system in subsonic and low supersonic flow regimes is analyzed using continuation method conjunction with an adaptive step size control algorithm. Idealizing pylon nacelle as point mass, computed effects standard structural analysis wing together are compared those clean to build reduced-order model for analysis. The aerodynamic forces relating different reduced frequencies assessed Doublet Lattice Method (DLM) regime lifting surface theory relying on unsteady linearized small-disturbance potential regime. Rational Function Approximation (RFA) then utilized state-space formulation equations, appended flutter prediction. Thereafter, equations resolved size, results which matched obtained from traditional p - k emphasize that exhibits distinct advantage achieving better accuracy estimating speed identifying “mode switching” phenomenon.