Detailed measurements, including surface-pressure distributions, shock-wave photographs and observations of boundary-layer separation, have been made over a wide range of incidence in the National Physical Laboratory ...
Observations made in the viscous sub-layer of turbulent shear flows with small surface pitot-tubes and hot wires show that such instruments give accurate values of boundaryiayer skin friction, at least in zero pressure ...
Control reversal due to deformation of a wing with a partial-span flap and inset aileron is considered theoretically for the particular case of a flap held at the root end. The semi-rigid method is used. An investigation ...
The development of the method of the measurement of admittances and the solution of the frequency equation for a complex full-scale airframe-engine system is given, dividing the dynamical system at the attachment of the ...
The potential flow, both with and without circulation, around several thin aeroplane wings has been studied by means of a three-dimensional potential analyser. It is shown that, by using the normal assumptions made in the ...
This paper is concerned with the formation of basic differential equations for the determination of the stress distribution in reinforced monocoque flat-sided structures, such as rectangular or polygonal fuselages and wing ...
This paper gives and applies a method of estimating the stresses caused by root constraint in a two-spar swept wing of reinforced monocoque construction where the ribs are parallel to the line of flight. The general scheme ...
A special nozzle has been made with associated ducting and instruments in order to provide an absolute measure of airflow. The equipment could form a portable self-contained assembly, enabling calibrations to be made of ...
The Report discusses briefly the philosophy of parametric methods of load measurement in which load is not measured directly, but is deduced from a statistical correlation with an appropriate combination of aircraft motion ...
A series of tests Was undertaken on a simple, two-dimensional, variable Mach-number effuser, or nozzle, designed for the range of supersonic flows up to Mach number 3.0. The performance of the nozzle was assessed from the ...
Small-scale injector units have been developed for providing the engine nacelles of V/STOL models, with both intake and exit flows. The primary energy supply was cold compressed air at pressure ratios up to 4:1. With the ...
The development of removable slotted liners to extend the range of the Royal Aircraft Establishment 3-ft Supersonic Wind Tunnel at Bedford to transonic speeds is described. The liners are mounted within the existing ...
A brief description is given of a technique using a differential microphone to measure the sound field structure within the duct of a rotor. The advantages and problems of direct in-duct, as opposed to far-field, measurement ...
To present the general theory of diffusion of antisymmetrical concentrated end loads and edge loads into parallel stiffened panels, including the theory of bending of a parallel stiffened panel under arbitrary transverse ...
A theoretical investigation is made into the diffusion of symmetrical, concentrated loads into a long stiffened panel having constant stress edge members and a transverse loading beam. Both pin-jointed and clamped end ...
In Part 1, the rigorous and the 'stringer-sheet' stress solutions are given for a point load applied in the plane of a semi-infinite sheet and at a finite distance from the boundary which is assumed to be free. From these ...
A detailed description is given of a computer program for analysing the inviscid, subsonic compressible pressure distributions around the blades of axial, radial and mixed-flow turbomachines. The flow equations are combined ...
A detailed description is given of the development of a computer program for analysing the flow through axial, radial and mixed-flow turbomachines. The theory is based on the through-flow analysis given by Wu 1,2 and the ...
An integral equation is derived for the velocity on the surface of a given body of revolution or a given symmetrical profile in longitudinal flow, using the generation of a body by a vortex layer on its surface. The ...
A calculation method is described for unsteady, subsonic flow through an infinite, two-dimensional cascade of flat plate blades at zero mean incidence. The unsteady blade lift and moment, generated acoustic waves and shed ...