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.
Orthotropic panel flutter at arbitrary yaw angles - Experiment and correlation with theory.
Aerospace Sciences Meeting ; 1973 ; Washington, DC
1973-01-01
Conference paper
No indication
English