Abstract
We describe an experimental investigation into the nonlinear behavior of thin elastic panels in subsonic flow. Specially, an apparatus is detailed that supports a low aspect ratio panel by clamping it along the spanwise edges while leaving its leading and trailing edges free. Preliminary results are given for a 0.016 inch thick panel with an aspect ratio of 2.72. A pronounced, leading-edge divergence phenomenon was observed at nonzero angles of attack.
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