The laminar boundary layer with injection through a permeable wall

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dc.creator Stevenson, T. N.
dc.date 2014-11-25T15:57:24Z
dc.date 2014-11-25T15:57:24Z
dc.date 1961-01
dc.date.accessioned 2022-05-09T10:17:27Z
dc.date.available 2022-05-09T10:17:27Z
dc.identifier http://dspace.lib.cranfield.ac.uk/handle/1826/8812
dc.identifier.uri https://reports.aerade.cranfield.ac.uk/handle/1826.2/4812
dc.description The steady incompressible laminar boundary layer equations for a perfect gas with arbitrary distributions of wall temperature, main stream velocity and normal velocity at the wall are solved approximately by a method similar to that of Lighthill (1950). Equations for the skin friction and the rate of heat transfer are obtained. In order to assess the accuracy of these equations, solutions are presented and compared with exact solutions for wedge type flow with a wall temperature distribution such that the difference between the wall and the stream temperatures is proportional to a power of the distance from the leading edge. A Prandtl number of 0 7 is used. A solution for the skin friction with a constant normal velocity at the wall and constant main stream velocity is also presented. The method is probably accurate enough for engineering purposes in regions of negative pressure gradient. A solution for compressible flow using a similar method is outlined.
dc.language en
dc.publisher College of Aeronautics
dc.relation College of Aeronautics Reports
dc.relation 145
dc.relation COA/145
dc.title The laminar boundary layer with injection through a permeable wall
dc.type Report


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