A description is given of an arithmetical method for obtaining solutions for steady incompressible viscous flow at low Reynolds numbers in the form of expansions in powers of the Reynolds numbers. The method has been used ...
Methods are now available to calculate throughout the speed range the performance of all-moving wing-tip controls on flat-plate wings in inviscid flow, neglecting the shock waves in the transonic regime. The theory, with ...
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 ...
R. A. Fairthorne; G. J. Griffith; M. F. C. Woollett(1952)
This report sketches the scope and working of the punched-card installation in Mathematical Services Department, Royal Aircraft Establishment, during the period from 1945 to 1952. Types of work for which the equipment is ...
As part of a general investigation of tile use of spoilers for lateral control, flight tests were required on a Falcon with retractable circular-arc spoilers. In the first stage of the flight tests pilots' impressions and ...
The paper deals with a simple method of fixing transition by the injection of small air jets into a boundary layer from a row of surface holes, and describes experiments which establish the effectiveness of the method. A ...
Wind-tunnel tests are described in which suction is applied at perforated strips, as an alternative to porous strips or s]ots, in order to maintain a laminar boundary layer. A test was first carried out on a single row of ...
An analysis has been made of the full-scale measured drag and lift performance, data available on the Sunderland, Solent, Shetland, Sealand, Saro E.6/44 and Princess boat seaplanes, which all have hulls of fairly orthodox ...
Wind-tunnel test results for the flutter of a swept-back wing carrying a localised mass, and having symmetric or antisymmetric freedoms of the root, are given. The tests were made on a model wing of 23 deg sweepback, the ...
The problems of engine airflow representation in wind-tunnel models are reviewed. Methods which have been used satisfactorily in low subsonic tunnels are described briefly. Special difficulties associated with testing at ...
Two rectangular wings of aspect ratio 4 were flutter tested in a supersonic wind tunnel at Mach numbers 1.6 and 2.0 using a technique in which a structural stiffness was varied to give flutter at the Mach number. The results ...
In view of the possibility of trimming some swept-wing aircraft at incidences above the stall, there has been a desire to visualise the whole pattern of vortex sheets and separated flow starting from the stalling wing, and ...
The methods of wave-drag estimation known as the area rule and transfer rule are restricted to non-lifting combinations of thin wings and slender bodies. The Lomax-Heaslet multipole method is applicable to configurations ...
The area-rule, moment of area-rule and transfer-rule methods for estimating the wave drag Of wing-body combinations are discussed. It is pointed out that the moment of area rule and the transfer rule are different forms ...
The paper presents systematic tables of formulae whose purpose is to facilitate the operational solution of response problems reducible to linear differential equations with constant coefficients and with simple forcing ...
The investigation of the fatigue and corrosion-fatigue resistance of special bronzes (Gough and Sopwith, 1937) is extended to include (1) aluminium bronze (D.T.D.I60), (2) beryllium bronze (2.25 per cent. Be), each in two ...
This paper gives the results of an investigation into the effects of wing torsion in a ternary-type spring tab flutter. The results presented are for a series of calculations on an idealised system having degrees of freedom ...
The post-buckling behaviour of a flat plate reinforced by stringers and frames is considered theoretically, attention being concentrated on the case of pure shear loading. Formulae and graphs are presented for the rapid ...
The paper is intended to give a complete optical theory of the Mach-Zehnder interferometer, without using difficult mathematical methods or complicated three-dimensional diagrams. The topics covered include the effect of ...
The report gives the results of tests to investigate the aerodynamic effects of aspect ratio on the flutter of delta wings that are virtually rigid but are flexibly supported at the root. A function representing the ...