Free Delivery Over $100
|
|
|||
|
||||
OverviewIn 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. Full Product DetailsAuthor: Chandra Shekar J , Kolakoti AdityaPublisher: LAP Lambert Academic Publishing Imprint: LAP Lambert Academic Publishing Dimensions: Width: 15.20cm , Height: 0.90cm , Length: 22.90cm Weight: 0.227kg ISBN: 9783659618895ISBN 10: 3659618896 Pages: 148 Publication Date: 31 October 2014 Audience: General/trade , General Format: Paperback Publisher's Status: Active Availability: In stock  We have confirmation that this item is in stock with the supplier. It will be ordered in for you and dispatched immediately. Table of ContentsReviewsAuthor InformationTab Content 6Author Website:Countries AvailableAll regions |
||||
