The report describes in detail the methods by which the principles of vortex-lattice theory, introduced in a previous report, R. & M. 1910, are applied to the calculation of the aerodynamic loading of wings by lifting-plane ...
The laminar boundary-layer equation, for a linearly retarded velocity in the main stream, U = 1 - 1/8x in reduced variables, has been solved numerically by working in finite intervals in x, with a correction for the finite ...
Using actuator-disc theory, simplified methods are given for the solution of the direct problem of the incompressible flow of air through an axial-flow turbo-machine. Calculations based on these methods are compared with ...
After the publication of a report (R. & M. 2631) on the derivation of airworthiness performance climb standards, various subsidiary points raised in the course of discussions were examined. Some of these have been collected ...
An extension of slender-wing theory, introduced by Adams and Sears, has been applied to some problems concerned with the properties of slender, lifting, wings with curved leading edges at supersonic speeds. Two particular ...
Some general solutions of the linearised equations of supersonic flow, in terms of Lamé functions, were obtained by G. M. Roper, using the methods of Robinson and Squire. The results were applied to calculate : (a) the ...
This Report describes an analysis of air resonance in the hover, and the solutions obtained for a helicopter with non-articulated blades. It is shown that stability in air resonance depends critically on blade structural ...
Some comprehensive calculations of the flow conditions resulting from the intersection of a weak shock wave with a strong shock are presented and discussed, for a range of upstream Mach numbers between 1.4 and 2.8. Such ...