Two-dimensional numerical analysis of active flow control by steady blowing along foil suction side by different urans turbulence models
The effects of active separation control by steady blowing jets were investigated numerically on three different examples: subsonic flow past Aerospatiale A airfoil at 13º angle-of-attack, transonic flow past NACA 0012 airfoil at 4º angle-ofattack, and transonic flow in linear compressor/turbine cas...
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VINCA Institute of Nuclear Sciences
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doaj-562c432cf4ef42778e2c52e38fb6face2021-01-02T12:16:40ZengVINCA Institute of Nuclear SciencesThermal Science0354-98362334-71632017-01-0121suppl. 364966210.2298/TSCI160126188S0354-98361600188STwo-dimensional numerical analysis of active flow control by steady blowing along foil suction side by different urans turbulence modelsSvorcan Jelena M.0Fotev Vasko G.1Petrović Nebojša B.2Stupar Slobodan N.3Faculty of Mechanical Engineering, Department of Aerospace Engineering, BelgradeFaculty of Mechanical Engineering, Department of Aerospace Engineering, BelgradeFaculty of Mechanical Engineering, Department of Aerospace Engineering, BelgradeFaculty of Mechanical Engineering, Department of Aerospace Engineering, BelgradeThe effects of active separation control by steady blowing jets were investigated numerically on three different examples: subsonic flow past Aerospatiale A airfoil at 13º angle-of-attack, transonic flow past NACA 0012 airfoil at 4º angle-ofattack, and transonic flow in linear compressor/turbine cascade. Performed analyses are two-dimensional, flow is turbulent (or transitional) while fluid is viscous and compressible. Jets are positioned along the suction sides of the foils, the first one being located just upstream of the separation point, and modeled by source terms added to flow equations. Several different jet diameters and intensities are investigated. As the choice of turbulence model affects the final solution of Reynolds equations, turbulence is modeled by four different models: Spalart- Allmaras, realizable k-ε, k-ω SST, and γ-Reθ, and a comparison of obtained results is performed. Goals of the study include definition of an adequate numerical setting that enables sufficiently correct simulation of the problems in question as well as evaluation of the possible increase in aerodynamic performances. Lift coefficients, lift-to-drag ratios or relative pressure differences are improved for all controlled cases.http://www.doiserbia.nb.rs/img/doi/0354-9836/2017/0354-98361600188S.pdfcomputational aerodynamicsturbulence modelsairfoil cascadesactive boundary layer controlsteady blowing |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Svorcan Jelena M. Fotev Vasko G. Petrović Nebojša B. Stupar Slobodan N. |
spellingShingle |
Svorcan Jelena M. Fotev Vasko G. Petrović Nebojša B. Stupar Slobodan N. Two-dimensional numerical analysis of active flow control by steady blowing along foil suction side by different urans turbulence models Thermal Science computational aerodynamics turbulence models airfoil cascades active boundary layer control steady blowing |
author_facet |
Svorcan Jelena M. Fotev Vasko G. Petrović Nebojša B. Stupar Slobodan N. |
author_sort |
Svorcan Jelena M. |
title |
Two-dimensional numerical analysis of active flow control by steady blowing along foil suction side by different urans turbulence models |
title_short |
Two-dimensional numerical analysis of active flow control by steady blowing along foil suction side by different urans turbulence models |
title_full |
Two-dimensional numerical analysis of active flow control by steady blowing along foil suction side by different urans turbulence models |
title_fullStr |
Two-dimensional numerical analysis of active flow control by steady blowing along foil suction side by different urans turbulence models |
title_full_unstemmed |
Two-dimensional numerical analysis of active flow control by steady blowing along foil suction side by different urans turbulence models |
title_sort |
two-dimensional numerical analysis of active flow control by steady blowing along foil suction side by different urans turbulence models |
publisher |
VINCA Institute of Nuclear Sciences |
series |
Thermal Science |
issn |
0354-9836 2334-7163 |
publishDate |
2017-01-01 |
description |
The effects of active separation control by steady blowing jets were investigated numerically on three different examples: subsonic flow past Aerospatiale A airfoil at 13º angle-of-attack, transonic flow past NACA 0012 airfoil at 4º angle-ofattack, and transonic flow in linear compressor/turbine cascade. Performed analyses are two-dimensional, flow is turbulent (or transitional) while fluid is viscous and compressible. Jets are positioned along the suction sides of the foils, the first one being located just upstream of the separation point, and modeled by source terms added to flow equations. Several different jet diameters and intensities are investigated. As the choice of turbulence model affects the final solution of Reynolds equations, turbulence is modeled by four different models: Spalart- Allmaras, realizable k-ε, k-ω SST, and γ-Reθ, and a comparison of obtained results is performed. Goals of the study include definition of an adequate numerical setting that enables sufficiently correct simulation of the problems in question as well as evaluation of the possible increase in aerodynamic performances. Lift coefficients, lift-to-drag ratios or relative pressure differences are improved for all controlled cases. |
topic |
computational aerodynamics turbulence models airfoil cascades active boundary layer control steady blowing |
url |
http://www.doiserbia.nb.rs/img/doi/0354-9836/2017/0354-98361600188S.pdf |
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