This paper presents the computational aeroelastic results generated in support of the second Aeroelastic Prediction Workshop for the Benchmark Supercritical Wing (BSCW) configurations and compares them to the experimental data. The computational results are obtained using FUN3D, an unstructured grid Reynolds- Averaged Navier-Stokes solver developed at NASA Langley Research Center. The analysis results include aerodynamic coefficients and surface pressures obtained for steady-state, static aeroelastic equilibrium, and unsteady flow due to a pitching wing or flutter prediction. Frequency response functions of the pressure coefficients with respect to the angular displacement are computed and compared with the experimental data. The effects of spatial and temporal convergence on the computational results are examined.
FUN3D Analyses in Support of the Second Aeroelastic Prediction Workshop
AIAA Aeroelastic Prediction Workshop (AePW-2)
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2016
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San Diego, CA, United States
AIAA Aviation Technology, Integration, and Operations Conference (Aviation 2016)
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2016
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Washington, DC, United States
AIAA Science and Technology Forum and Exposition (SciTech 2016)
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2016
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San Diego, CA, United States
2016-06-13
Conference paper
No indication
English
FUN3D Analyses in Support of the Second Aeroelastic Prediction Workshop (AIAA 2016-3122)
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