Abstract
Aeroelastic computations are made for a flexible wing with a tip-propeller system designed for electric aircraft. Flow is modeled using the Navier–Stokes equations, and wing structures are modeled using plate finite elements. A time-accurate procedure is developed to embed the flexible wing in an overset grid topology along with rotating blades. Results are validated with existing data from wind-tunnel and potential flow computations. Aeroelastic responses are compared for the wing with and without a tip-propeller system. The present work extends the capabilities of current Navier–Stokes solvers to simulate the aeroelasticity of complex configurations and impacts the design of electric aircraft for urban transportation.
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