AbstractIn this study, the nonlinear aeroelastic characteristics of a wing with an oscillating control surface have been examined in transonic and supersonic regimes. The various effects of rotational stiffness on flutter have also been observed. A modified transonic small-disturbance (TSD) theory is used to more effectively analyze the unsteady aerodynamics of a wing with an oscillating control surface. In the flutter analysis, a coupled time integration method (CTIM) and a transient pulse method (TPM) were used to examine the effects of rotational stiffness reduction on the control surface. The present study shows that the severe decrease of flutter speed and the flutter mode transition can be induced by the reduction of rotational stiffness. In particular, it is shown that the aerodynamic effects of control surface oscillation play an important role in this flutter speed reduction.
Frequency and time domain flutter computations of a wing with oscillating control surface including shock interference effects
Aerospace Science and Technology ; 8 , 6 ; 519-532
2004-04-05
14 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Transonic Flutter Computations for a 2D Supercritical Wing
British Library Conference Proceedings | 1999
|NTRS | 1997
NTIS | 1997