Отрывок: 15, chord Reynolds number equal to 6 Mil- lion and the angle of attack equal to 10 degrees. For Sutherland’s Model the reference viscosity and temperature are 1.865·10-5 kg/ms 300 K, respectively and at the far stream boundary the turbulent initial value is set using an initial turbulent viscosity ratio equal to 0.210438. The air- foil surface is modeled as a wall with no slip and adiabatic conditions. For the Spalart-Allmaras Model a Prandtl Number of 0.72 is used, a...
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dc.contributor.authorMéndez Soto, M.A.-
dc.contributor.authorPorfiriev, D.P.-
dc.date.accessioned2016-12-14 14:13:05-
dc.date.available2016-12-14 14:13:05-
dc.date.issued2016-
dc.identifierDspace\SGAU\20161214\60849ru
dc.identifier.citationМатериалы Международной конференции и молодёжной школы «Информационные технологии и нанотехнологии», с. 804-810ru
dc.identifier.isbn978-5-7883-1078-7-
dc.identifier.urihttp://repo.ssau.ru/handle/Informacionnye-tehnologii-i-nanotehnologii/Numerical-study-of-the-aerodynamic-performance-of-NACA-0012-in-the-presence-of-an-unsteady-heat-source-60849-
dc.description.abstractThe objective of this paper is to study the effect of an unsteady moving heat source on the aerodynamic performance of an NACA 0012 airfoil section, with particular focus on the lift and drag coefficients. The compressible Navier–Stokes equations are solved using a finite volume method as well as Spalart-Allmaras Model for turbulence simulation. The heat source periodically moves over the lower surface of the airfoil in the downstream direction. The numerical results show how the drag and lift coefficient strongly depend upon the velocity of the source. For a constant source power, a progressive improvement in the mean values of lift and drag coefficients is observed as velocity increases.ru
dc.language.isoenru
dc.publisherИздательство СГАУru
dc.subjectaerodynamic performanceru
dc.subjectheat sourceru
dc.subjectlift coefficientru
dc.subjectdrag coefficientru
dc.subjectcomputational fluid dynamicsru
dc.titleNumerical study of the aerodynamic performance of NACA 0012 in the presence of an unsteady heat sourceru
dc.typeArticleru
dc.textpart15, chord Reynolds number equal to 6 Mil- lion and the angle of attack equal to 10 degrees. For Sutherland’s Model the reference viscosity and temperature are 1.865·10-5 kg/ms 300 K, respectively and at the far stream boundary the turbulent initial value is set using an initial turbulent viscosity ratio equal to 0.210438. The air- foil surface is modeled as a wall with no slip and adiabatic conditions. For the Spalart-Allmaras Model a Prandtl Number of 0.72 is used, a...-
Располагается в коллекциях: Информационные технологии и нанотехнологии

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