TY - JOUR
T1 - Numerical simulation of transitional flow on a wind turbine airfoil with RANS-based transition model
AU - Zhang, Ye
AU - Sun, Zhengzhong
AU - van Zuijlen, Alexander
AU - van Bussel, Gerard
PY - 2017/6/1
Y1 - 2017/6/1
N2 - This paper presents a numerical investigation of transitional flow on the wind turbine airfoil DU91-W2-250 with chord-based Reynolds number Rec = 1.0 × 106. The Reynolds-averaged Navier–Stokes based transition model using laminar kinetic energy concept, namely the k − kL − ω model, is employed to resolve the boundary layer transition. Some ambiguities for this model are discussed and it is further implemented into OpenFOAM-2.1.1. The k − kL − ω model is first validated through the chosen wind turbine airfoil at the angle of attack (AoA) of 6.24° against wind tunnel measurement, where lift and drag coefficients, surface pressure distribution and transition location are compared. In order to reveal the transitional flow on the airfoil, the mean boundary layer profiles in three zones, namely the laminar, transitional and fully turbulent regimes, are investigated. Observation of flow at the transition location identifies the laminar separation bubble. The AoA effect on boundary layer transition over wind turbine airfoil is also studied. Increasing the AoA from −3° to 10°, the laminar separation bubble moves upstream and reduces in size, which is in close agreement with wind tunnel measurement.
AB - This paper presents a numerical investigation of transitional flow on the wind turbine airfoil DU91-W2-250 with chord-based Reynolds number Rec = 1.0 × 106. The Reynolds-averaged Navier–Stokes based transition model using laminar kinetic energy concept, namely the k − kL − ω model, is employed to resolve the boundary layer transition. Some ambiguities for this model are discussed and it is further implemented into OpenFOAM-2.1.1. The k − kL − ω model is first validated through the chosen wind turbine airfoil at the angle of attack (AoA) of 6.24° against wind tunnel measurement, where lift and drag coefficients, surface pressure distribution and transition location are compared. In order to reveal the transitional flow on the airfoil, the mean boundary layer profiles in three zones, namely the laminar, transitional and fully turbulent regimes, are investigated. Observation of flow at the transition location identifies the laminar separation bubble. The AoA effect on boundary layer transition over wind turbine airfoil is also studied. Increasing the AoA from −3° to 10°, the laminar separation bubble moves upstream and reduces in size, which is in close agreement with wind tunnel measurement.
KW - Boundary layer transition
KW - laminar kinetic energy
KW - laminar separation bubble
KW - RANS modelling
KW - wind turbine aerodynamics
UR - http://www.scopus.com/inward/record.url?scp=85020483763&partnerID=8YFLogxK
U2 - 10.1080/14685248.2017.1334908
DO - 10.1080/14685248.2017.1334908
M3 - Article
AN - SCOPUS:85020483763
SN - 1468-5248
VL - 18
SP - 879
EP - 898
JO - Journal of Turbulence
JF - Journal of Turbulence
IS - 9
ER -