In the present study, the numerical study is carried out for boundary layer flow over 3D aerofoil section and the aerodynamic performance of NACA aerofoil are analyzed by studying the lift and drag coefficient of the aerofoil.The results obtained in the case of boundary layer flow over the 3D aerofoil section are compared with the experimental data as available in the literature. The experimental data for NACA 64-009 from wind tunnel is validated with simulations results computed in FLUENT. The aerofoil is cambered and measured to be around 1mt. The simulations for boundary layer flow for NACA 64-009 is performed at various angles of attacks. In addition, the lift coefficient, drag coefficient, pressure contour and velocity contour are computed.
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In the present study, the numerical study is carried out for boundary layer flow over 3D aerofoil section and the aerodynamic performance of NACA aerofoil are analyzed by studying the lift and drag coefficient of the aerofoil.The results obtained in the case of boundary layer flow over the 3D aerofoil section are compared with the experimental data as available in the literature. The experimental data for NACA 64-009 from wind tunnel is validated with simulations results computed in FLUENT. The aerofoil is cambered and measured to be around 1mt. The simulations for boundary layer flow for NACA 64-009 is performed at various angles of attacks. In addition, the lift coefficient, drag coefficient, pressure contour and velocity contour are computed.
Mr. J. Chandra Shekar completed his Masters Degree in CAD/CAM.Have professional experience of 3.10 years as Design Engineer.Proficient in Design Tools like CATIA-V5R19 and AutoCAD-2009.Proficient in Meshing Tool like ICEM-CFD 10/13.
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Librería: BuchWeltWeit Ludwig Meier e.K., Bergisch Gladbach, Alemania
Taschenbuch. Condición: Neu. This item is printed on demand - it takes 3-4 days longer - Neuware -In the present study, the numerical study is carried out for boundary layer flow over 3D aerofoil section and the aerodynamic performance of NACA aerofoil are analyzed by studying the lift and drag coefficient of the aerofoil.The results obtained in the case of boundary layer flow over the 3D aerofoil section are compared with the experimental data as available in the literature. The experimental data for NACA 64-009 from wind tunnel is validated with simulations results computed in FLUENT. The aerofoil is cambered and measured to be around 1mt. The simulations for boundary layer flow for NACA 64-009 is performed at various angles of attacks. In addition, the lift coefficient, drag coefficient, pressure contour and velocity contour are computed. 148 pp. Englisch. Nº de ref. del artículo: 9783659618895
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Librería: moluna, Greven, Alemania
Condición: New. Dieser Artikel ist ein Print on Demand Artikel und wird nach Ihrer Bestellung fuer Sie gedruckt. Autor/Autorin: Chandra Shekar J.Mr. J. Chandra Shekar completed his Masters Degree in CAD/CAM.Have professional experience of 3.10 years as Design Engineer.Proficient in Design Tools like CATIA-V5R19 and AutoCAD-2009.Proficient in Meshing Tool like. Nº de ref. del artículo: 5168779
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Librería: buchversandmimpf2000, Emtmannsberg, BAYE, Alemania
Taschenbuch. Condición: Neu. This item is printed on demand - Print on Demand Titel. Neuware -In the present study, the numerical study is carried out for boundary layer flow over 3D aerofoil section and the aerodynamic performance of NACA aerofoil are analyzed by studying the lift and drag coefficient of the aerofoil.The results obtained in the case of boundary layer flow over the 3D aerofoil section are compared with the experimental data as available in the literature. The experimental data for NACA 64-009 from wind tunnel is validated with simulations results computed in FLUENT. The aerofoil is cambered and measured to be around 1mt. The simulations for boundary layer flow for NACA 64-009 is performed at various angles of attacks. In addition, the lift coefficient, drag coefficient, pressure contour and velocity contour are computed.Books on Demand GmbH, Überseering 33, 22297 Hamburg 148 pp. Englisch. Nº de ref. del artículo: 9783659618895
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Librería: preigu, Osnabrück, Alemania
Taschenbuch. Condición: Neu. Numerical Analysis of Boundary Layer Flow Over 3D Aerofoil Section | CFD Analysis | J. Chandra Shekar (u. a.) | Taschenbuch | 148 S. | Englisch | 2014 | LAP LAMBERT Academic Publishing | EAN 9783659618895 | Verantwortliche Person für die EU: BoD - Books on Demand, In de Tarpen 42, 22848 Norderstedt, info[at]bod[dot]de | Anbieter: preigu. Nº de ref. del artículo: 105002763
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Librería: AHA-BUCH GmbH, Einbeck, Alemania
Taschenbuch. Condición: Neu. nach der Bestellung gedruckt Neuware - Printed after ordering - In the present study, the numerical study is carried out for boundary layer flow over 3D aerofoil section and the aerodynamic performance of NACA aerofoil are analyzed by studying the lift and drag coefficient of the aerofoil.The results obtained in the case of boundary layer flow over the 3D aerofoil section are compared with the experimental data as available in the literature. The experimental data for NACA 64-009 from wind tunnel is validated with simulations results computed in FLUENT. The aerofoil is cambered and measured to be around 1mt. The simulations for boundary layer flow for NACA 64-009 is performed at various angles of attacks. In addition, the lift coefficient, drag coefficient, pressure contour and velocity contour are computed. Nº de ref. del artículo: 9783659618895
Cantidad disponible: 1 disponibles
Librería: Mispah books, Redhill, SURRE, Reino Unido
Paperback. Condición: Like New. Like New. book. Nº de ref. del artículo: ERICA79736596188966
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