Aeronautical Research Council: Recent submissions

Now showing items 281-300 of 2786

Some possible effects of transonic speeds on wing-aileron flutter

E. G. Broadbent; E. Violet Hartley (1959)

A typical wing-aileron combination is taken and ternary flutter calculations between wing bending, wing torsion and aileron rotation are described. The results are plotted as graphs of flutter speed against aileron frequency ...
A note on flutter of asymmetric controls

E. G. Broadbent; E. V. Hartley (1960)

This Paper attempts to give some guidance on the question, of how best to approximate to an aircraft with an asymmetric elevator control for the purpose of flutter calculations. Two examples of asymmetric controls that ...
Published reports and memoranda of the Aeronautical Research Council

Unknown author (1962)

This paper lists one hundred titles which have been published in the R. & M. Series of the Aeronautical Research Council. The Council number is included for the purpose of record only.
Force and moment coefficients for vibrating aerofoils in cascade

D. S. Whitehead (1960)

This Report gives a method for calculating the aerodynamic forces and moments acting on unstalled vibrating cascade blades. The forces and moments due to both bending and torsional vibration are calculated, and also due ...
Turbulent wall jets with and without an external stream

P. Bradshaw; M. T. Gee (1960)

The results are presented of experiments on wall jets in still air on flat and curved surfaces, and beneath an external stream in presence and absence of pressure gradient and initial boundary layer. It is found that the ...
The analysis of blade vibration due to random excitation

D. S. Whitehead (1960)

This Report gives an account of the experimental measurement of the power spectra of waveforms derived from vibrating blades in axial compressors under running conditions. This enables the damping factor of the blades to ...
Properties of a two-parameter family of thin conically cambered delta wings by slender-body theory

J. C. Cooke (1960)

Slender theory with exact boundary conditions is used to calculate the flow past a thin conically cambered delta wing. The (spanwise) camber-line consists of a straight central part with two drooping pieces at the sides, ...
High-speed Wind-tunnel Tests on Models of Four Single-engined Fighters (Spitfire, Spiteful, Attacker and Mustang) Parts 1-5

W. A. Mair et al (1945)

Part I - Tests on the Spitfire I. Part II - Tests on the Spiteful (F. 1/43). Part III - Tests on Cabins for the Spiteful. Part IV - Tests on the Attacker (E. 10/44). Part V - Tests on the Mustang I. This report describes ...
Part I. A Description of the Excitation and Recording Equipment used for Flight Flutter Tests on a Meteor 8. Part II. Comparative Flight Flutter Tests using the 'Decaying Oscillation' and 'Amplitude Response' Techniques

P. D. R. Luscombe; W. T. Kirkby (1959)

A description is given of the installation Of a single linear inertia exciter and multichannel recording equipment which was fitted to a Meteor aircraft for use in the development of flight flutter test techniques. The ...
Behaviour of skin fatigue cracks at the corners of windows in a Comet I fuselage

R. J. Atkinson; W. J. Winkworth; G. M. Norris (1960)

Fatigue tests on a Comet I pressure cabin subjected to operational pressure cycles are described. Cracks at window corners are the main subject of investigation. Results are compared with earlier experiments on other Comet ...
Pressure distribution and surface flow on 5 percent and 9 percent thick wings with curved tip and 60 degrees sweepback

H. C. Garner; D. E. Walshe (1960)

Extensive tables are given of pressure coefficients measured at Reynolds numbers from 1.3 x 10power6 to 3.9 x 10power6 on two half-models of identical planform with 5% RAE 101 and 9% RAE 101 streamwise sections. The planform ...
An Experimental Investigation of Heat Transfer from the Inside Surface of a Hot Smooth Tube to Air, Helium and Carbon Dioxide

J. F. Barnes (1960)

This Report gives experimental values of Nusselt number as a function of Reynolds number and surface/gas temperature ratio for three gases, air, helium and carbon dioxide, and shows the effects of radial variations of fluid ...
Thermal buckling of circular plates

B. Cotterell; E. W. Parkes (1960)

The post-buckling behaviour of a circular plate is investigated for two conditions--heating over the centre and heating at the edge. In the former case the plate buckles into the form of a saucer; in the latter into a ...
An approximate integral method for calculating the incompressible laminar boundary layer on an infinite swept wing on which velocity and suction distribution are arbitrary

H. G. Pinsent; P. A. Pinsent (1959)

Summary. The method described in this Report gives an approximate solution for the cross-flow velocity in an incompressible laminar boundary layer on an infinite swept wing. The cross flow is defined as that velocity in ...
The Flow past a Pitot Tube at Low Reynolds Numbers. Part I. The Numerical Solution of the Navier-Stokes Equations for Steady Viscous Axi-symmetric Flow. Part II. The Effects of Viscosity and Orifice Size on a Pitot Tube at Low Reynolds Numbers

W. G. S. Lester (1960)

Part I. In this Report numerical methods used to solve the Navier-Stokes equations for steady viscous two-dimensional flow are extended to include the case of axial symmetry. The equations and their finite difference ...
Some convergence problems in the numerical solution of the navier-stokes equations

W. G. S. Lester (1960)

The convergence of numerical solutions of the Navier-Stokes equations for steady two-dimensional flow is examined and convergence criteria for both ψ and ζ are obtained for a rectangular mesh. The criterion for ψ is shown ...
Flight tests to investigate the dynamic lateral-stability characteristics of a 45-deg delta, cropped to give three aspect ratios

J. E. Nethaway; J. Clark (1960)

Flight tests to determine the dynamic lateral-stability characteristics of the Boulton-Paul IIIA aircraft have been made at aspect ratios 3.8, 3.0 and 2.3. They showed that the changes in damping, period and phase angle ...
The test performance of highly loaded turbine stages designed for high pressure ratio

I. H. Johnston; D. C. Dransfield (1959)

A blade design for a highly loaded two-stage turbine is described and the test performance of the turbine is presented. Some of the factors affecting the performance and matching of turbine blade rows operating at supersonic ...
Measurement of pitching-moment derivatives for aerofoils oscillating in two-dimensional supersonic flow

C. Scruton; L. Woodgate; K. C. Lapworth; J. Maybrey (1959)

Pitching-moment derivatives have been measured by a free oscillation technique on two-dimensional aerofoils of double wedge section with thickness/chord ratios of 0.08, 0.12 and 0.16; and on an aerofoil of single wedge ...
The pressure distribution on two-dimensional wings near the ground

J. A. Bagley (1960)

A simple method of calculating the pressure distribution in incompressible flow on two-dimensional aerofoils of arbitrary section at moderate distances from the ground is developed. Comparisons with an 'exact' potential-flow ...

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