Frequency and time domain flutter computations of a wing with oscillating control surface including shock interference effects

In 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. (C) 2004 Elsevier SAS. All rights reserved.
Publisher
ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER
Issue Date
2004-09
Language
ENG
Keywords

AEROELASTIC ANALYSIS; TRANSONIC FLOW; FLAP; AIRFOIL

Citation

AEROSPACE SCIENCE AND TECHNOLOGY, v.8, no.6, pp.519 - 532

ISSN
1270-9638
DOI
10.1016/j.ast.2004.04.001
URI
http://hdl.handle.net/10203/5586
Appears in Collection
AE-Journal Papers(저널논문)
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