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 flow solver developed at the NASA Langley Research Center. Flutter analyses are performed using various aerodynamic models including linear doublet lattice, Euler solutions, Reynolds averaged Navier-Stokes and Delayed Detached Eddy Simulations. The analyses are performed across the transonic Mach range for a range in angle of attack from 0° to 5°, with focus on identifying the transonic dips in the flutter onset boundaries.
Predicting Transonic Flutter Using Nonlinear Computational Simulations
International Forum on Aeroelasticity and Structural Dynamics (IFASD 2019) ; 2019 ; Savannah, GA, United States
2019-06-10
Aufsatz (Konferenz)
Keine Angabe
Englisch
Nonlinear transonic flutter analysis
AIAA | 1981
|Nonlinear transonic flutter analysis
AIAA | 1982
|