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 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 focus on understanding the dip in the transonic flutter boundary at a single Mach number (0.74), exploring an angle of attack range of 1 to 8 and dynamic pressures from wind off to beyond flutter onset. The rigid analysis results are examined for insights into the behavior of the aeroelastic system. Both static and dynamic aeroelastic simulation results are also examined.
Investigating the Transonic Flutter Boundary of the Benchmark Supercritical Wing
2017
24 pages
Report
No indication
English
Aircraft , Test Facilities & Equipment , Fluid Mechanics , Computer Software , Aeroelasticity , Angle of attack , Supercritical wings , Transonic flutter , Boundary layers , Boundary layer flow , Computational fluid dynamics , Computational grids , Computerized simulation , Dynamic structural analysis , Rigid wings , Structural stability , Aerodynamic characteristics , Aerodynamic configurations , Computer programs , Grid refinement (mathematics) , Navier-stokes equation , Reynolds averaging , Stiffness , Wing planforms
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