Numerical simulation of transonic buffet on a laminar airfoil was performed. The transonic air flow over a wing with the chord of 70 mm was computed (M∞ = 0.628-0.73) at different angles of attack α = 3.5°-7°. Numerical simulation was performed by solving the two-dimensional unsteady Navier-Stokes equations using the ANSYS Fluent package. Two different turbulence models were used: Transition SST (k-w-γ-ReΘ) and k-w SST turbulence model. The computational domain corresponded to the geometry of the test section of the aerodynamic wind tunnel T-325 ITAMSBRAS. In the numerical simulation two periodic non-stationary processes were detected. The first is associated with the pulsations generated in the separation zone that occurs when the shock wave interacts with the boundary layer. This process is characterized by frequencies from 4 to 4.8 kHz, depending on the Mach number and the angle of attack of the wing. The second more lower-frequency non-stationary process with a frequency of ∼200 Hz is associated with the periodic movement of the separation point. Computational results were compared with experimental data.
Numerical simulation of transonic buffeting on laminar airfoil
INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2020) ; 2020 ; Novosibirsk, Russia
AIP Conference Proceedings ; 2351 , 1
2021-05-24
4 pages
Conference paper
Electronic Resource
English
Airfoil Unsteady Aeroelastic Responses in Buffeting Transonic Flows
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