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, sa.10, ss.2155-2164, 2010 (SCI-Expanded) identifier identifier

  • Yayın Türü: Makale / Tam Makale
  • Cilt numarası: 224 Sayı: 10
  • Basım Tarihi: 2010
  • Doi Numarası: 10.1243/09544062jmes2121
  • Dergi Adı: Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science
  • Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus
  • Sayfa Sayıları: ss.2155-2164
  • Anahtar Kelimeler: aerodynamics, computational fluid dynamics, laminar separation bubble, stall, thin aerofoil, transition model, INTERMITTENCY TRANSPORT-EQUATION, BYPASS TRANSITION, TURBULENCE MODEL, LOCAL VARIABLES, BOUNDARY-LAYERS, LAMINAR, AIRFOIL, SUCTION
  • Erciyes Üniversitesi Adresli: Evet

Özet

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-ω shear-stress transport (SST) transition models, recently developed, and k-ω SST and k-e turbulence models. Subsonic flow with free streamMach number (M8) 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-ω SST transition model and the k-ω SST and k-e 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.