Although a modal transformation is often employed to simplify the solution for the aeroelastic eigenvalue problem, modal derivatives are frequently ignored in deriving the aeroelastic eigenvalue derivatives. The complete flutter derivatives are derived in general here and applied in particular to the cases of quasi-steady aerodynamic strip theory and unsteady doublet lattice panel theory. Results for an unswept isotropic wing model demonstrate that the modal derivative terms may in fact be significant. An alternative approach in which the structural modes are treated as a basis for the flutter is shown to provide derivatives with comparable accuracy.
Effect of modal sensitivity of flutter eigenvalue derivatives
Einfluß der modalen Empfindlichkeit auf die Eigenwertableitungen des Flatterns
1994
7 Seiten, 4 Bilder, 7 Tabellen, 10 Quellen
Conference paper
English
EIGENVALUE AND FLUTTER SENSITIVITY ANALYSIS OF AIRLINER WING
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