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

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概要

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• 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.

著者

• ISOGAI Koji

  Structures Research Group, Japan Aerospace Exploration Agency

関連論文

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

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