期刊
AIAA JOURNAL
卷 57, 期 8, 页码 3200-3205出版社
AMER INST AERONAUTICS ASTRONAUTICS
DOI: 10.2514/1.J058610
关键词
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资金
- NASA Advanced Supercomputing Division
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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