Wind Tunnel Experiments on an Actively Controlled,Variable Geometry Flutter Model.

摘要

A reduction in flutter margin can occur for variable geometry aircraft when the wing of the aircraft is swept into the vicinity of the tail. Experiments on an aeroelastic wind tunnel model with active aerodynamic controls demonstrated that the flutter margins of these configurations can be increased through techniques other than the standard structural modifications. Improved margins were attained experimentally by employing rapidly responding aerodynamic controls activated by an optimal feedback. (Author)