Measurements have been made of the direct tab derivatives and cross aileron-tab derivatives for a 1541 section two-dimensional aerofoil (N.P.L. 282) with a 20 per cent aileron and 4 per cent (approx.) tab. In addition some ...
Tests on NACA 0020 sections of 1.2 and 2.0-in. chord completely spanning the tunnel showed that there was no appreciable difference in compressibility drag rise due to wind-tunnel interference. This was the case both with ...
The development of actuator-disc theory and its application to predict the flow through axial-flow turbo-machines has been given in Ref. I. An investigation of the accuracy of these theoretical predictions of performance ...
When a pitot-tube is used in a pipe or boundary layer, the shear and the presence of the wall may cause the pressure in the tube to differ from the true total pressure on the axis of the tube. To investigate these effects, ...
The velocity distribution around the nose of an NACA 0015-64 aerofoil was found by experiment and that around the nose of a Piercy 15/40 aerofoil by calculation for various angles of incidence and flap deflection. It was ...
Relationships have been derived for expressing the velocities on three-dimensional tapered wings at zero incidence in terms of the velocities on untapered infinite swept wings. The theoretical investigation of the effects ...
Real flow patterns are produced by formally placing a pair of conjugate complex sources at conjugate complex points on the axis of symmetry. These complex singularities are shown to be equivalent to a non-uniform distribution ...
Tests have been made with distributed suction applied to a short-span sleeve fitted to the upper surface of the wing of a single-seat Vampire aircraft. Full-chord laminar flow was maintained up to Reynolds numbers in the ...
The initial lift for wings of finite aspect ratio due to a sudden unit change of incidence is considered and, by the use of the method developed in R. & M. 21171, the ratio of the initial to the final values of the lift ...
This report, which is presented in two parts, develops an approximate method of estimating the effect of structural deformability on the manoeuvre point of an aircraft. The introduction outlines the scope of the complete ...
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 ...
The effect of changes in the shape of the windscreen on the drag of a cockpit canopy has been measured on models in free flight. Canopies were attached to the models by means of a flexible mounting in such a way as to allow ...
An approximate method of estimating the effect of the ground on the lift of a rotor at any forward speed is described. Flight tests on several different helicopters show reasonable agreement with the theory. Curves are ...
The degree of cooling that might be achieved in gas-turbine blades with simple internal air-cooling is surveyed with a view to pin-pointing the essential requirements for effective cooling with small quantities of cooling ...
Enthalpy charts have been constructed to facilitate dealing with the thermodynamic problems of combustion and flow of dissociating gases within the temperature range of 600 deg to 4,000 deg K. By means of a quantity called ...
Results of research work done in this country and the subject matter of Refs. 1 to 4 on the measurement and analysis of the air drag of seaplane hulls are collected together in this report. The data consist of the results ...
A general investigation has been made into measurement, control and performance problems associated with boat seaplane take-off and initial climb. Particular attention was paid to engine failure during take-off and initial ...
The paths of the cores of the vortex sheets shed from the wings of a typical guided-missile model, having cruciform rectangular wings mounted on a long cone-cylinder body, have been traced in their movement downstream over ...
A specially designed rudder has been fitted to a Vampire Mk. 5 to act as an aerodynamic yaw damper. Flight tests show that the damping of the lateral oscillation has been substantially increased in consequence a logarithmic ...
This report is a continuation of four earlier ones by the present authors and contains a theoretical investigation of subsonic flow past thin tapered swept-back wings at zero incidence, by the first-order method. The basic ...