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Orthotropic panel flutter at arbitrary yaw angles - Experiment and correlation with theory
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1973
Year
AeroacousticsEngineeringPhysicsAerospace EngineeringMechanicsOrthotropic Panel FlutterMechanical EngineeringMechanical SystemsAeroelasticityAerodynamicsExperimental Flutter BoundariesFlutter SpeedsAircraft Design ProcessStructural MechanicsAerostructureFlutter BoundariesStructural EngineeringArbitrary Yaw Angles
Experimental flutter boundaries were obtained for yaw angles between 15 and 90 deg at Mach numbers 2 and 1.6 for panels mounted on a remotely controlled turntable. Good definition of the flutter boundaries was obtained by rotating the panels into and out of flutter. Two types of specimens were tested: a single-sheet corrugated panel having a length-to-width ratio of 5 on clamped supports, and several square doubly-corrugated panels on various flexible supports. Calculated flutter speeds based on quasi-steady aerodynamics are compared to experimental data.