23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-4.4.1 (I.L.)

AILERON FLUTTER CALCULATION FOR A SUPERSONIC FUSELAGE-WING CONFIGURATION

G. Yang (1), S. Obayashi (1), J. Nakamichi (2)
(1) Tohoku University, Japan; (2) National Aerospace Laboratory of Japan, Japan

Keywords: multiblock grid, numerical simulation, aeroelasticity, aileron buzz

A fully implicit multiblock aeroelastic solver, coupled thin-layer Navier-Stokes equations with structural equations of motion, has been developed for the flutter simulation on complex aerodynamic configurations. Navier-Stokes equations are solved with LU-SGS subiteration algorithm and a modified Harten-Lax-van Leer Einfeldt-Wada (HLLEW) scheme. Structural equations of motion are discretized by a direct second-order differential method with subiteration in generalized coordinates. The transfinite interpolation (TFI) is used for the grid deformation of the blocks neighboring the flexible surface. For the purpose of validation, the boundaries of the flutter speed and frequency of the AGARD 445.6 standard aeroelastic wing are first calculated. Then, the method is used for the prediction of the flutter boundaries of the NAL supersonic transport (SST) fuselage-wing configuration. Finally, for the same model, the aeroelastic instability referred to as aileron buzz is investigated.

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