Numerical simulation of flow over a thin aerofoil at a high Reynolds number using a transition model


Genc M. S.

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART C-JOURNAL OF MECHANICAL ENGINEERING SCIENCE, cilt.224, ss.2155-2164, 2010 (SCI İndekslerine Giren Dergi) identifier

  • Yayın Türü: Makale / Tam Makale
  • Cilt numarası: 224
  • Basım Tarihi: 2010
  • Doi Numarası: 10.1243/09544062jmes2121
  • Dergi Adı: PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART C-JOURNAL OF MECHANICAL ENGINEERING SCIENCE
  • Sayfa Sayıları: ss.2155-2164

Özet

In this study, a prediction of the transition and stall characteristics of an NACA64A006 thin-aerofoil was numerically simulated by FLUENT using k-k(L)-omega and k-omega shear-stress transport (SST) transition models, recently developed, and k-omega SST and k-epsilon turbulence models. Subsonic flow with free stream Mach number (M(infinity)) of 0.17 and the high Reynolds number (Re) of 5.8 x 10(6) was considered at an angle of attack varying from 2 degrees to 11 degrees. However, the computed results were compared with the experiments of McCollough and Gault. Lift and pressure curves were accurately predicted using the k-k(L)-omega transition model, while the k-omega SST transition model and the k-omega SST and k-epsilon turbulence models did not have a good agreement with the experimental results. The k-k(L)-omega transition model showed that the laminar separation and turbulent reattachment occurred near the leading edge of the NACA64A006 thin aerofoil, which caused the formation of the laminar separation bubble on the suction surface as in the experiments. Consequently, the transition and stalling characteristics of this aerofoil were successfully predicted using FLUENT with the k-k(L)-omega transition model at high Re number flow.
In this study, a prediction of the transition and stall characteristics of an NACA64A006 thin-aerofoil was numerically simulated by FLUENT using k—kL—? and k—? shear-stress transport (SST) transition models, recently developed, and k—? SST and k—? turbulence models. Subsonic flow with free stream Mach number (M?) of 0.17 and the high Reynolds number (Re) of 5.8×106 was considered at an angle of attack varying from 2° to 11°. However, the computed results were compared with the experiments of McCollough and Gault. Lift and pressure curves were accurately predicted using the k—kL—? transition model, while the k—? SST transition model and the k—? SST and k—? turbulence models did not have a good agreement with the experimental results. The k—kL—? transition model showed that the laminar separation and turbulent reattachment occurred near the leading edge of the NACA64A006 thin aerofoil, which caused the formation of the laminar separation bubble on the suction surface as in the experiments. Consequently, the transition and stalling characteristics of this aerofoil were successfully predicted using FLUENT with the k—kL—? transition model at high Re number flow.