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This is all largely over my head but the subject has been studied in depth/documented well and the material is available. I got a kick out of Dan Raymer's book "Simplified Aircraft Design for Homebuilders" The flutter section basically states "refer to a good reference on the subject when designing your plane" Hmmm..... I thought that's why I bought this book
Design of Light Aircraft by Richard D Hiscocks has a good section on flutter and stiffness. He worked at De Havilland and was involved in many of the aircraft they produced including the Beaver. I believe he also had a hand in the Murphy Aircraft designs (Rebel). Briefly reviewing the section several factors impact aileron flutter: wing stiffness in deflection and torsion, aileron torsional stiffness, aileron shape and hinge location, aileron center of mass/CG, control circuit stiffness, etc.
Flaps exist on a portion of the wing that moves less and is inherently more rigid. Ailerons are out further where the wing has the most deflection up/down and twisting.
The LSA ailerons may not be statically balanced on the hinge line but that doesn't mean a great deal of care wasn't placed in their static/dynamic balance.
Design of Light Aircraft by Richard D Hiscocks has a good section on flutter and stiffness. He worked at De Havilland and was involved in many of the aircraft they produced including the Beaver. I believe he also had a hand in the Murphy Aircraft designs (Rebel). Briefly reviewing the section several factors impact aileron flutter: wing stiffness in deflection and torsion, aileron torsional stiffness, aileron shape and hinge location, aileron center of mass/CG, control circuit stiffness, etc.
Flaps exist on a portion of the wing that moves less and is inherently more rigid. Ailerons are out further where the wing has the most deflection up/down and twisting.
The LSA ailerons may not be statically balanced on the hinge line but that doesn't mean a great deal of care wasn't placed in their static/dynamic balance.
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