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58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
An aeroelastic analysis of a prototype distributed electric propulsion wing is presented. Results using MSC Nastran™ doublet lattice aerodynamics are compared to those based on FUN3D Reynolds Averaged Navier-Stokes aerodynamics. Four levels of grid refinement were examined for the FUN3D solutions and solutions were seen to be well converged. It was found that no oscillatory instability existed, only that of divergence, which occurred in the first bending mode at a dynamic pressure of over threedoi:10.2514/6.2017-0413 fatcat:e3tveiajubemnbbl64vut6yhxu