A computational study of inviscid, transonic aileron and trailing-edge buzz instabilities is presented. A mixed Eulerian-Lagrangian formulation is used to model the fluid-structure system and to obtain a system of space-discretized equations that is time-marched to simulate the aeroelastic behavior of the wing-aileron system. Results obtained suggest that shock-induced separation may not be an essential driving force behind all buzz phenomena. Several examples are shown where the shock motion interacts with the aileron motion to extract energy from the flow. If the trailing-edge region is sufficiently flexible and the shocks are at the trailing edge, a trailing-edge buzz instability appears possible.
Nonclassical aileron buzz in transonic flow
AIAA, ASME, ASCE, AHS, and ASC, Structures, Structural Dynamics and Materials Conference, 34th and AIAA and ASME, Adaptive Structures Forum ; 1993 ; La Jolla, CA, United States
01.04.1993
Aufsatz (Konferenz)
Keine Angabe
Englisch
Nonclassical aileron buzz in transonic flow
AIAA | 1993
|Calculation of transonic aileron buzz
AIAA | 1979
|Calculation of transonic aileron buzz
Tema Archiv | 1980
|Calculation of transonic aileron buzz
Tema Archiv | 1979
|Calculation of Transonic Aileron Buzz
AIAA | 1980
|