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 13? angle-of-attack, transonic flow past NACA 0012 airfoil at 4? angle-ofattack, and transonic flow in linear compressor/turbine cas...

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Bibliographic Details
Published inThermal science Vol. 21; no. suppl. 3; pp. 649 - 662
Main Authors Svorcan, Jelena, Fotev, Vasko, Petrovic, Nebojsa, Stupar, Slobodan
Format Journal Article
LanguageEnglish
Published Belgrade Society of Thermal Engineers of Serbia 01.01.2017
Subjects
Active control
Aerodynamics
Blowing
Compressibility
Computational fluid dynamics
Computer simulation
Flow control
Flow equations
Fluid flow
Foils
Numerical analysis
Separation
Subsonic aircraft
Subsonic flow
Suction
Transonic flow
Turbines
Turbulence models
Turbulent flow
Two dimensional analysis
Two dimensional flow
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Summary:The effects of active separation control by steady blowing jets were investigated numerically on three different examples: subsonic flow past Aerospatiale A airfoil at 13? angle-of-attack, transonic flow past NACA 0012 airfoil at 4? 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-?, k-? SST, and ?-Re?, 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. nema
ISSN:0354-9836
2334-7163
DOI:10.2298/TSCI160126188S