Browsing by Author "Marshall, W. S. D."
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Item Open Access The determination in flight of the body drag and the mean blade profile drag coefficient of a helicopter(College of Aeronautics, Cranfield, 1952-04) Bartholomew, F. E.; Marshall, W. S. D.Slight modifications have been made to the energy equation which enables the results of partial climb tests to be plotted as two straight lines, the slopes of which are measures of the body drag of the helicopter and the mean profile drag coefficient of the rotor blades. Sufficient data has been analysed to show that the method can be used to obtain an accurate measurement of the body drag. Continues …Item Open Access The distribution of pressure over the surface of wings of small aspect ratio(College of Aeronautics, Cranfield, 1952-02) Marshall, W. S. D.The distribution of pressure over wings of aspect ratio 1.5 and 0.5 have been measure for a range of incidences up to and including the stall at various angles of yaw. This report presents a detailed analysis of the results at two incidences corresponding to ¼ and ¾ of the stalling incidences approximately. Continues …Item Open Access Some experiments on the flow in the boundary layer of a 45 degrees sweptback untapered wing of aspect ratio 4(College of Aeronautics, Cranfield, 1953-02) Emslie, K.; Hosking, L.; Marshall, W. S. D.Visual methods have been used together with a yawmeter to illustrate conditions of flow in the boundary layer over a sweptback wing. It was found out that at moderate incidences a marked outflow in the boundary layer was developed. Continues …Item Open Access The use of a potential flow tank for testing axi-symmetric contraction shapes suitable for wind tunnels(College of Aeronautics, Cranfield., 1951-04) Babister, A. W.; Marshall, W. S. D.; Lilley, G. M.; Sills, E. C.; Deards, S. R.The report gives details of tests in the potential flow tank on a series of axi-symmetric contraction shapes. The tests were in connection with the design of the 8ft x 6ft wind tunnel and a water tunnel. Continues...