24th Congress of International Council of the Aeronautical Sciences, 29 August-3, September 2004, Yokohama, Japan
Paper ICAS 2004-5.8.1 (I.L.)

A FLUTTER MODEL FOR ROTOR BLADES WITH FLAPS

M. A. Couch, E. R. Wood*
U.S. Navy/COMSEVENTHFLT, USA; *Naval Postgraduate School, USA

Keywords: Flutter, Rotor Blades, Flaps, Aeroelasticity

Lagrange’s equation is applied to a 5DOF rotor blade system with trailing-edge flaps to develop a flutter solution. Three-dimensional aspects are included with sectional variations of mass, geometry and freestream velocity. Aerodynamic effects are examined through different lift deficiency functions. Practical application is demonstrated using a hingeless rotor blade.

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