Evaluation of the turbulence models for the simulation of the flow over a Tsentralniy Aerogidrodinamicheskey institut (TsAGI)-12% Airfoil

International Journal of Mechanical Engineering
© 2017 by SSRG - IJME Journal
Volume 4 Issue 1
Year of Publication : 2017
Authors : Nishant Kumar, Saurav Upadhaya, Ashish Rohilla
How to Cite?

Nishant Kumar, Saurav Upadhaya, Ashish Rohilla, "Evaluation of the turbulence models for the simulation of the flow over a Tsentralniy Aerogidrodinamicheskey institut (TsAGI)-12% Airfoil," SSRG International Journal of Mechanical Engineering, vol. 4,  no. 1, pp. 18-28, 2017. Crossref, https://doi.org/10.14445/23488360/IJME-V4I1P104


The numerical analysis of the two-dimensional subsonic flow over a Tsentralniy Aerogidrodinamicheskey institut ―B series (TsAGI) -12% airfoil at an assorted angle of attack (AOA) and flow operating at a Reynolds number of 1×106 is proposed. The flow is established by employing the steady-state governing equation of continuity and momentum conservation conflated with one of the four turbulence models [Spalart-Allmaras (1 equation),Standard k-ε (2 equation), k-ω standard (2 equation) and Transition SST (4 equation)]. The intention of the study is to demonstrate the behaviour of the Airfoil at different turbulence models as mentioned furthermore, in addition, to obtain a verified solution method. The computational domain is composed of 43584 structured cells. In order, to properly capture the boundary layer, refinement of the grid near the Airfoil is done. The calculations were made by fixing the velocity (14.6122449 m/s) of the flow at a fixed Reynolds number Re= 1×106 and altering the only angle of attack (AOA). The presented work demonstrated the coefficient of lift and coefficient of drag at different turbulence models, at varying angle of attack. In addition, the work also emphasizes that at higher AOA, the turbulence models used in commercial CFD, yet not able to produce accurate results.


Computational Fluid Dynamics (CFD), Coefficient of Drag (Cd),Turbulence models, Boundary layer, Numerical Analysis, Subsonic, Airfoil.


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