Effect of Turbulence Models on Simulated Iced Aircraft Airfoil
The present work describes a computational study of
aerodynamic characteristics of GLC305 airfoil clean and with 16.7
min ice shape (rime 212) and 22.5 min ice shape (glaze 944).The
performance of turbulence models SA, Kε, Kω Std, and Kω SST
model are observed against experimental flow fields at different
Mach numbers 0.12, 0.21, 0.28 in a range of Reynolds numbers
3x106, 6x106, and 10.5x106 on clean and iced aircraft airfoil
GLC305. Numerical predictions include lift, drag and pitching
moment coefficients at different Mach numbers and at different angle
of attacks were done. Accuracy of solutions with respect to the
effects of turbulence models, variation of Mach number, initial
conditions, grid resolution and grid spacing near the wall made the
study much sensitive. Navier Stokes equation based computational
technique is used. Results are very close to the experimental results.
It has seen that SA and SST models are more efficient than Kε and
Kω standard in under study problem.
[1] Kevin R. Petty* and Carol D. J. Floyd National Transportation Safety
Board, Washington, DC.
[2] Chi, X., Zhu, B.Shih, T.I-P., Slater, J.W., Addy, H.E., and Choo, Y.K.,
"Computing Aerodynamic Performance of 2D Iced Airfoils" Blocking
Topology and Grid Generation." AIAA Paper 2002-0381, January 2002
[3] Addy, H.E, "Iced Accretions and Icing Effects for Modern Airfoils",
NASA/TP-2000-210031, April 2000
[4] Addy, H.E., " A Wind Tunel Study of Icing Effects on a Business Jet
Airfoil" NASA/TM-2003-212124, AIAA Paper 2003-0727, February
2003 Lax, P.D. " Weak Solution of Nonlinear Hyperbolic Equation and
their Numerical Computation" Comm. Pure and Applied Mathematics,
7(1954), pp.159-193
[5] Zierep,J.: Vorlesungen uber theoretische Gasdynamik(Lectures on
Theoretical Gas Dynamics). G.Braun Verlag, Karlaruhe, 1963
[6] Liepmann, HG.W.; Roshko, A. "Elements of Gas Dynamics". John
Wiley & Sons, New York, 1957
[7] Bertin. John J. "Aerodynamics for engineers" 2nd ed. TL570.B42 1989,
ISBN 0-13-01843-
[8] Spalart, S.R.; Allmaras, S.A. "A One-Equation Turbulence Model for
Aerodynamic Flows". AIAA Paper 92-0439, 1992; also in La Recherche
Aerospatiale, 1 (1994), pp. 5-21
[9] Menter, F.R. "Two-Equation Eddy-Viscosity Turbulence Models for
Eingeering Applications" AIAA paper 93-2906, 1993; also AIAA
Journal, 32(1994), pp.1598-1605
[1] Kevin R. Petty* and Carol D. J. Floyd National Transportation Safety
Board, Washington, DC.
[2] Chi, X., Zhu, B.Shih, T.I-P., Slater, J.W., Addy, H.E., and Choo, Y.K.,
"Computing Aerodynamic Performance of 2D Iced Airfoils" Blocking
Topology and Grid Generation." AIAA Paper 2002-0381, January 2002
[3] Addy, H.E, "Iced Accretions and Icing Effects for Modern Airfoils",
NASA/TP-2000-210031, April 2000
[4] Addy, H.E., " A Wind Tunel Study of Icing Effects on a Business Jet
Airfoil" NASA/TM-2003-212124, AIAA Paper 2003-0727, February
2003 Lax, P.D. " Weak Solution of Nonlinear Hyperbolic Equation and
their Numerical Computation" Comm. Pure and Applied Mathematics,
7(1954), pp.159-193
[5] Zierep,J.: Vorlesungen uber theoretische Gasdynamik(Lectures on
Theoretical Gas Dynamics). G.Braun Verlag, Karlaruhe, 1963
[6] Liepmann, HG.W.; Roshko, A. "Elements of Gas Dynamics". John
Wiley & Sons, New York, 1957
[7] Bertin. John J. "Aerodynamics for engineers" 2nd ed. TL570.B42 1989,
ISBN 0-13-01843-
[8] Spalart, S.R.; Allmaras, S.A. "A One-Equation Turbulence Model for
Aerodynamic Flows". AIAA Paper 92-0439, 1992; also in La Recherche
Aerospatiale, 1 (1994), pp. 5-21
[9] Menter, F.R. "Two-Equation Eddy-Viscosity Turbulence Models for
Eingeering Applications" AIAA paper 93-2906, 1993; also AIAA
Journal, 32(1994), pp.1598-1605
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:50305", author = "Muhammad Afzal and Cao Yihua and Zhao Ming", title = "Effect of Turbulence Models on Simulated Iced Aircraft Airfoil", abstract = "The present work describes a computational study of
aerodynamic characteristics of GLC305 airfoil clean and with 16.7
min ice shape (rime 212) and 22.5 min ice shape (glaze 944).The
performance of turbulence models SA, Kε, Kω Std, and Kω SST
model are observed against experimental flow fields at different
Mach numbers 0.12, 0.21, 0.28 in a range of Reynolds numbers
3x106, 6x106, and 10.5x106 on clean and iced aircraft airfoil
GLC305. Numerical predictions include lift, drag and pitching
moment coefficients at different Mach numbers and at different angle
of attacks were done. Accuracy of solutions with respect to the
effects of turbulence models, variation of Mach number, initial
conditions, grid resolution and grid spacing near the wall made the
study much sensitive. Navier Stokes equation based computational
technique is used. Results are very close to the experimental results.
It has seen that SA and SST models are more efficient than Kε and
Kω standard in under study problem.", keywords = "Aerodynamics, Airfoil GLC305, Iced Airfoil,Turbulence Model", volume = "5", number = "8", pages = "1556-8", }