numerical analysis boundary layer de chandra shekar (6 resultados)

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.

Paperback. Condición: Like New. LIKE NEW. SHIPS FROM MULTIPLE LOCATIONS. book.

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.

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.

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.

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.