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 ...
The report describes experiments devised to investigate some of the previously unexplained peculiarities of normal types of pitot-static tube. Revised basic calibration factors for various instruments are recorded. In the ...
The paper presents a review of recent experimental and theoretical research on two-dimensional base flows. The main object is to illustrate the extent to which the basic properties of the flow are understood in each of the ...
The function of the manometer is to enable small pressure differences to be measured at a distance. The instrument will measure either the difference of two pressures or a single pressure relative to atmosphere. The accurate ...
Some measurements of downwash have been made in a plane behind a 12-ft diameter helicopter rotor over a range of shaft inclination and tip speed ratio. In the various operating conditions, the tunnel tests are in reasonable ...
The drag increase beyond the critical Mach number is calculated by modifying the supersonic part of the Karman-Tsien pressure distribution on a profile. This is possible when the supersonic regions are not too large. The ...