The tail-first aeroplane has certain strong attractions when combined with a tricycle undercarriage; in particular it has been suggested that it would represent a definite advance in the production of high lift. In these ...
Very little has been recorded during the war years as to the details of technique used in low-speed wind-tunnel tests. The size and type of tunnel used during this period will remain in use at firms and colleges for some ...
These notes aim at providing a framework to display what is known of the backward movement of the aerodynamic centre of wing shapes likely to be used for transonic operation, as the flow progresses from incompressible ...
Summary. A brief review of oscillatory theories reveals that some of these suffer from a defect that has been corrected in the Algol programme now subject to critical examination. Its features in steady and low-frequency ...
The previous work of the author in which the subcritical flow past ellipsoids was calculated is extended to supercritical flows. The same ellipsoidal coordinate system is used, the body-surface boundary-condition is then ...
The problem of a subcritical, potential, steady, three-dimensional flow past an unyawed ellipsoid is considered, using ellipsoidal coordinates. The full equations of motion and the exact body surface boundary condition are ...
Numerical solutions of the energy-balance equation of an axially symmetrical uniform arc column are outlined and illustrated with results pertaining to a nitrogen plasma at atmospheric pressure. Published data on the ...
The characteristic 'N' shaped pressure waves recorded at ground level below the flight path of supersonic aircraft have compressive regions very much less steep than predicted by theory, with a consequent reduction in the ...
Summary. The equations of motion for supersonic flow over a symmetrical wing at zero incidence are linearised and the pressure coefficient at a point in the wing mean plane is expressed in terms of the finite part of a ...
The number of available exact solutions of the full equations of motion of an incompressible viscous fluid is remarkably few. Those that exist are mostly limited to steady flows. Where a steady state solution does exist, ...
A method is presented for calculating steady axially symmetric spiralling motions of an incompressible fluid at large Reynolds numbers. By making approximations of the boundary-layer type the Navier-Stokes equations are ...
Introduction and Summary.--Recent advances in electronic computing devices suggest that it may soon be feasible to attempt numerical solutions of problems involving three independent variables. In this paper, preliminary ...
Numerical methods are given for calculating the double integral ... for the three cases: (i) F(x) is given numerically, (ii) F(x) is the first derivative of a numerically given function, (iii) F(x) is the second derivative ...
Knowledge of the pressure distribution on a body moving in a fluid is required in a variety of applications, such as the prediction of cavitation inception conditions and the study of boundary-layer development. For many ...
Methods are given in this paper of dealing with singularities of functions satisfying certain two dimensional partial differential equations. For a numerical solution the differential equations are replaced by difference ...
Part I. A solution of lift interference in oscillatory incompressible flow is described. Both steady and unsteady interference parameters are determined from a complete solution of the complex velocity potential, which is ...
Flow photographs and detailed pressure distributions for a 4 per cent thick circular-arc biconvex aerofoil at transonic speeds are presented. The results for incidences of 0, 1, 2 and 5 deg are analysed in detail.
Flow photographs and detailed pressure distributions for a 4 per cent thick circular-arc biconvex aerofoil at high subsonic speeds and high incidences have been analysed and the divergence boundary (defining the onset of ...
Direct-shadow and schlieren photographs and pressure distributions of the flow past a two-dimensional 4 per cent thick biconvex aerofoil for a limited range of incidences at Mach numbers of 1.40 and 1.63 are presented. ...
Photographs have been taken of the flow round a 10 per cent thick RAE 104 aerofoil performing pitching oscillations at low values of the frequency parameter (ω < 0.1) in subsonic and supersonic air streams. Apart from a ...