Numerical investigation on the aeroelastic instability of a complete aircraft model

A nonlinear aeroelastic analysis system has been developed using the coupled numerical techniques of computational fluid dynamics (CFD) and computational structural dynamics (CSD) in the present study and the analysis system has been applied to an actual aircraft design procedure to examine aeroelastic stabilities. An aerodynamic analysis is performed using the transonic small disturbance (TSD) theory for computational efficiency and the results are compared with experimental data. An aeroelastic analysis in the time domain is performed to obtain the flutter boundaries of the aircraft model. Finally, the various effects of launchers and control surfaces are investigated.
Publisher
JAPAN SOC MECHANICAL ENGINEERS
Issue Date
2005-05
Language
ENG
Keywords

COMPUTATIONS

Citation

JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING , v.48, no.2, pp.212 - 217

ISSN
1340-8054
URI
http://hdl.handle.net/10203/6605
Appears in Collection
AE-Journal Papers(저널논문)
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