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.


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    Title :

    Orthotropic panel flutter at arbitrary yaw angles - Experiment and correlation with theory.


    Contributors:

    Conference:

    Aerospace Sciences Meeting ; 1973 ; Washington, DC


    Publication date :

    1973-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English