A study of the aeroelastic behavior of flat plates and membranes with mixed boundary conditions in axial subsonic flow
In support of the noise reduction targets for future generations of transport aircraft, as set forth by NASA, the fundamental aeroelastic behavior of trailing edge flap technology was explored. Using a plate structural model to approximate the structural configuration and linear potential flow theory to represent the aerodynamics, aeroelastic behavior was characterized for two structural configurations: all edges simply supported and leading and side edges simply supported trailing edge free. Results are compared to calculations presented in the literature for all edges simply supported configurations. Copyright © 2011 by the American Institute of Aeronautics and Astronautics, Inc.