Print Email Facebook Twitter Three-dimensional laminar boundary-layer separation on a flat plate due to a flow confrontation with a half cone at incidence Title Three-dimensional laminar boundary-layer separation on a flat plate due to a flow confrontation with a half cone at incidence Author Shen, P.S. Jones, D.J. Institution National Research Council Canada, National Aeronautical Establishment, High Speed Aerodynamics Section Date 1967-06-30 Abstract The incompressible, three-dimensional, laminar boundary layer flow on a flat plate about a half-cone protuberance has been investigated bath by experiment in the NAE water tunnel and by analysis using Cooke's small cross-flow momentum integral method. Three half cones of semi-apex angles 7½, 10° and 12½, were tested at a Reynolds number of 2 x 104 based on plate chord. Reasonable agreement between computed and measured limiting surface streamlines and primary separation lines was found. but the inclusion of the thickness effect of the half cone in the potential model of tbe external flow was found te be important. To reference this document use: http://resolver.tudelft.nl/uuid:9a4ec440-15bc-4a3d-8a24-01e5cf21e9ce Publisher National Research Council Canada Access restriction Campus only Source National Research Council Aeronautical Report LR 485 Part of collection Aerospace Engineering Reports Document type report Rights (c)1967 National Research Council Canada Files PDF LR-485.pdf 4.01 MB Close viewer /islandora/object/uuid:9a4ec440-15bc-4a3d-8a24-01e5cf21e9ce/datastream/OBJ/view