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Transitional CFD Investigation of Stepped Airfoil

DOI: 10.1615/ICHMT.2012.ProcSevIntSympTurbHeatTransfPal.2190
pages 2125-2132

S. Sammak
Aerospace Engineering Department, Amirkabir University of Technology, Tehran, Iran

R. Mojgani
Aerospace Engineering Department, Amirkabir University of Technology, Tehran, Iran

Masoud Boroomand
Aerospace Engineering Department, Amirkabir University of Technology, Tehran, Iran


This study presents the Computational Fluid Dynamic of simulation of flow around NLF(1)-0416 airfoil which utilized the backward facing step to investigate enhancement of aerodynamic characteristic. This article concentrate on the effects of step location transition point and reattachment of separated flow by backward facing step on pressure distribution and subsequently on lift and drag coefficient. Reynolds number that based on the free stream velocity and airfoil chord is 2.0 million. The finite volume method has been employed to numerically solve the steady state compressible Reynolds averaged Navier Stokes (RANS) equations with second order Roe’s scheme. Steps are located on both suction side and pressure side of the airfoil, at different locations, in order to determine their effects on lift, lift to drag ratio and near stall behavior. In some case decreasing in drag is achieved due to step point on the chord followed by transition inception. The modeling results showed that all stepped airfoil cases studied experienced higher drag by comparison with base airfoil. Significant lift to drag ratio enhancement is seen in step on pressure side while the step extended to leading edge, this effect increases. Based on the result, delaying stall in some cases with step on suction surface is concluded.

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