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 ...
Theoretical solutions of near wake flow have been obtained by application of the particle-in-cell numerical teohnique to hypersonic flow over the base of a cylindrical afterbody. Using the invisoid equations of motion and ...
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 ...
A specially developed pressure-measuring instrument has been used to observe instantaneous values of the pressure, velocity and direction of the flow in a single stage, low hub-tip ratio, axial compressor. During stall ...
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 ...