Numerical Investigations of the Benchmark Supercritical Wing in Transonic Flow
| Autor: | Pawel Chwalowski, Robert T. Biedron, Jennifer Heeg |
|---|---|
| Rok vydání: | 2017 |
| Předmět: |
020301 aerospace & aeronautics
Engineering Wing business.industry Angle of attack 02 engineering and technology Mechanics Aeroelasticity 01 natural sciences 010305 fluids & plasmas Physics::Fluid Dynamics symbols.namesake 0203 mechanical engineering Mach number 0103 physical sciences symbols Flutter Dynamic pressure Pitch angle Aerospace engineering business Transonic |
| Zdroj: | 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. |
| DOI: | 10.2514/6.2017-0190 |
| Popis: | This paper builds on the computational aeroelastic results published previously and generated in support of the second Aeroelastic Prediction Workshop for the NASA Benchmark Supercritical Wing (BSCW) configuration. The computational results are obtained using FUN3D, an unstructured grid Reynolds-Averaged Navier-Stokes solver developed at the NASA Langley Research Center. The analysis results show the effects of the temporal and spatial resolution, the coupling scheme between the flow and the structural solvers, and the initial excitation conditions on the numerical flutter onset. Depending on the free stream condition and the angle of attack, the above parameters do affect the flutter onset. Two conditions are analyzed: Mach 0.74 with angle of attack 0 and Mach 0.85 with angle of attack 5. The results are presented in the form of the damping values computed from the wing pitch angle response as a function of the dynamic pressure or in the form of dynamic pressure as a function of the Mach number. |
| Databáze: | OpenAIRE |
| Externí odkaz: |
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