Numerical and experimental modelling of transition in a separated boundary layer on the NACA63A421 airfoil

0353754 - ÚT 2011 CZ eng K - Konferenční příspěvek (tuzemská konf.)
Ďuriš, M. - Popelka, Lukáš - Příhoda, Jaromír - Šimurda, David
Numerical and experimental modelling of transition in a separated boundary layer on the NACA63A421 airfoil.
HYDRO/TERMO – XXIX. setkání kateder mechaniky tekutin a termomechaniky. Ostrava: VŠB- Technická univerzita Ostrava, 2010 - (Dvořák, L.; Fojtášek, K.; Krutil, J.; Zavadil, L.), s. 45-48. ISBN 978-80-248-2244-0.
[Setkání kateder mechaniky tekutin a termomechaniky /29./. Rožnov pod Radhoštěm (CZ), 23.06.2010-25.06.2010]
Grant CEP: GA MŠMT(CZ) 1M06031; GA ČR GA103/09/0977
Výzkumný záměr: CEZ:AV0Z20760514
Klíčová slova: laminar separated bubble * transition modelling
Kód oboru RIV: BK - Mechanika tekutin

The paper is concerned with numerical modelling of transition in a separated boundary layer. A transition model is based on the combination of empirical terms determining position of the transition and averaged Navier–Stokes equations closed by SST turbulence model. The model of transition is applied in computation of 2D flow past NACA63A421 airfoil. Computation is performed using commercial code Fluent 6.3.26, in which the transition model is implemented as a User-Defined-Function. Computed distributions of the pressure coefficient along the airfoil are verified by comparison with experimental data, which were obtained by measurements in a closed circuit wind tunnel at the constant Reynolds number and several angles of attack. The comparison proves the applicability of the implemented transition model.
Trvalý link: http://hdl.handle.net/11104/0192909