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Comparison between SST and k-ε Models for the Computation of 3-D Flow past Isolated NACA Blade Profiles

DOI: 10.1615/ICHMT.2006.TurbulHeatMassTransf.750
pages 381-384

B. Noura
Mechanical Engineering School, USTH.B. University of Technology, P.B. 32, El Alia Bab Ezzouar, 16111 Algiers, Algeria

Rabah Dizene
Mechanical Engineering Department, Advanced Mechanics Laboratory, University of USTHB, ALGERIA

Djamel Cherrarred
Advanced Mechanics Laboratory, USTH.B. University of Technology, P.B. 32, El Alia Bab Ezzouar, 16111 Algiers, Algeria

E. G. Filali
Advanced Mechanics Laboratory, USTH.B. University of Technology, P.B. 32, El Alia Bab Ezzouar, 16111 Algiers, Algeria

Said Benmansour
Advanced Mechanics Laboratory, USTH.B. University of Technology, P.B. 32, El Alia Bab Ezzouar, 16111 Algiers, Algeria

Sinopsis

Compressible solutions of Reynolds-averaged Navier-Stokes equations are found for three-dimensional flow past an isolated NACA blades using several turbulence models: two-equation models and Reynolds stress models which are currently being tried out for the computation of flow past airfoils. Numerical results on the behaviour of NACA 0012, NACA 7512 and NACA 6512 at high chord Reynolds number are presented for 0.45 and 0.85 Mach number values. The focus is devoted to the comparison between model results particularly for stall conditions corresponding to separated flow. All the calculations have been performed using CFX 5.7.1® code. It is found that the Shear Stress Transport (SST) model resolves the passage vortex better on the suction side of the profiles.

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