Browsing by Author "Kirkby, S."
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Item Open Access Application of the linear perturbation theory to compressible flow about bodies of revolution(College of Aeronautics, Cranfield, 1947-09) Young, A. D.; Kirkby, S.The linearised theory is developed in some detail in order to clarify the differences between two-dimensional and axi-symmetric flow. In agreement with other authors it is concluded that the perturbation velocity on a thin body of revolution in compressible flow is 1/β2 times the perturbation velocity in incompressible flow on a thinner body at reduced incidence obtained by reducing the lateral dimensions of the original body in the ratio (3:1). This result is applied to a representative family of streamline bodies of revolution at zero incidence. Continues…Item Open Access The numerical solution of certain differential equations occurring in Crocco's theory of the laminar boundary layer(College of Aeronautics, Cranfield, 1953-05) Kirkby, S.; Nonweiler, T.A numerical method is described for the solution of certain differential equations which result from the application of Crocco’s transformation to the laminar boundary layer equations appropriate to high supersonic Mach numbers. (i.e. at hypersonic speeds). Continues …Item Open Access The relative accuracy of quadrature formulae of the Cotes' closed type(College of Aeronautics, Cranfield, 1948-05) Kirkby, S.Quadrature formulae, such as those discovered by Gregory, Newton, Simpson and Cotes, which are derivable by integration of Lagrange’s interpolation formula between definite limits, are classified as Cotes’ Type Formulae. When the functional values at the end –points of the range of integration are used the corresponding formulae are said to be of the ‘closed type’. It is shown that, for closed type formulae, the error due to application of a 2n-strip formula is in general less than that due to a (2n+a) –strip formula over the same range of integration when using the same tabular interval of the argument.Item Open Access Wing body interference at supersonic speeds(College of Aeronautics, Cranfield, 1947-04) Kirkby, S.; Robinson, A.The increment in lift due to wing-body interference at supersonic speed is calculated approximately for an untapered wing without sweepback.