Numerical Simulation of Shock-Stall Flutter of a High-Aspect-Ratio Forward-Swept Wing

Numerical Simulation of Shock-Stall Flutter of a High-Aspect-Ratio Forward-Swept Wing

In order to understand the unusual flutter phenomenon observed in experimental transonic flow for a high-aspect-ratio forward-swept wing, numerical simulations are conducted using a 3D Navier-Stokes code. The simulations confirm that the flutter is a single-degree-of-freedom flutter of the first ben...

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Veröffentlicht in:TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 2013, Vol.56(5), pp.303-311
1. Verfasser: ISOGAI, Koji
Format: Artikel
Sprache:eng
Schlagworte:
Bending
CFD
Computer simulation
Flutter
Forward-Swept Wing
Mathematical models
Navier-Stokes equations
Shock Stall
Three dimensional
Transonic Flutter
Vibration
Wings (aircraft)
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Zusammenfassung:In order to understand the unusual flutter phenomenon observed in experimental transonic flow for a high-aspect-ratio forward-swept wing, numerical simulations are conducted using a 3D Navier-Stokes code. The simulations confirm that the flutter is a single-degree-of-freedom flutter of the first bending mode in which shock-induced flow separation plays a dominant role. The simulations also clarify the detailed effects of Mach number and dynamic pressure (particularly the mass ratio) on this type of flutter.
ISSN:0549-3811
2189-4205
DOI:10.2322/tjsass.56.303