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Improvements in the fatigue strength of joints by the use of interference fits

W. A. P. Fisher; W. J. Winkworth (1952)

A study is made of the effect of interference fit in loaded holes on the fatigue strength of the associated part. Fatigue-test results are given for aluminium alloy fiat bars with a single hole loaded by a pin in double ...

The effect of tight clamping on the fatigue strength of joints

W. A. P. Fisher; W. J. Winkworth (1952)

The effect of clamping on the fatigue strength of joints in aluminium alloy is investigated experimentally. Tests on Z-section stringers connected to long, slotted cleats give an endurance for tightly clamped joints about ...

Interference velocity for a close pair of contra-rotating airscrews

C. N. H. Lock (1941)

A method is developed of calculating the performance of a pair of contra-rotating airscrews, closely analogous to that described in R. & M. 2035 a for a single airscrew. The assumptions made are considered to be theoretically ...

A simplified treatment of a fixed-root swept wing built on Hill's isoclinic principle

D. Williams (1951)

This note shows how the Hill Aero-isoclinic Principle works out in practice for a swept wing, fixed at the root and having straight flexural and inertia axes. The conditions assumed are readily represented in a wind-tunnel ...

The theory of torsional vibrations of a four-boom thin-walled cylinder of rectangular cross-section

E. H. Mansfield (1951)

The,torsional vibrations of a four-boom cylinder of doubiy symmetrical rectangular cross-section are considered and the differential equation of motion is derived on the assumption that the ribs maintain the section shape ...

The flutter properties of a simple aero-isoclinic wing system

N. C. Lambourne; A. Chinneck (1950)

The work dealt with in this report is of an exploratory nature primarily intended to provide some understanding of the flutter characteristics of a Hill aero-isoclinic wing. Essentially, this is a swept-back wing elastically ...

Flutter and resonance characteristics of a model cantilever wing carrying localised masses

N. C. Lambourne (1951)

Resonance tests on a model cantilever wing carrying concentrated masses were made in conjunction with the flutter tests of R. & M. 2533. Measurements were made with masses up to approximately five times the mass of the ...

Water performance of a four-engined flying boat with step fairings of length 3, 6 and 9 times the step depth

G. J. Evans; A. G. Smith; R. A. Shaw; W. Morris (1941)

Tests were made to investigate the hydrodynamic qualities of the Sunderland flying boat, when fitted with step fairings of mean gradient 1 : 3, 1 : 6 and 1 : 9. Attitude and acce]eration measurements were made during ...

Force and moment measurements on a conical body and a rectangular wing, separately and in combination, at Mach number 1.94

J. R. Anderson; D. Treadgold (1951)

Results are given of wind-tunnel measurements at M = 1.94 of lift, drag and pitching moment at small angles of incidence on two cones, three rectangular wings and on the six derived cone-wing combinations. A description ...

Tests at high subsonic speeds on a 10 per cent thick pressure-plotting aerofoil of RAE 104 section

E. W. E. Rogers; C. J. Berry; R. F. Cash (1951)

1. Summary and Introduction.--A series of tests has been made in the National Physical Laboratory 20-in. x 8-in. High Speed Wind Tunnel on a two-dimensional pressure-plotting aerofoil of five inches chord and RAE 104 ...

Helicopter rotor behaviour after engine failure in forward flight

W. Stewart; M. F. Burle (1951)

Calculations have been made to find the changes in rotor speed following engine failure in forward flight. Several particular examples were investigated, based on the parameters of the S-81 helicopter. The effect of pilot's ...

Some applications of the lamé function solutions of the linearised supersonic flow equations. Part I. Finite swept-back wings with symmetrical sections and rounded leading edges. Part II. Cambered and twisted wings

G. M. Roper (1951)

Some general solutions of the linearised equations of supersonic flow, in terms of Lamé functions, were obtained by G. M. Roper, using the methods of Robinson and Squire. The results were applied to calculate : (a) the ...

Assessment of the relative performance of the by-pass engine and the orthodox double compound jet engine

E. A. Bridle (1948)

The by-pass engine can be described as a form of ducted fan engine in which the fan boosts the main compressor. Two possible forms of by-pass engine are described, and their estimated performance is compared with that of ...

Investigation of the flow past finite wedges of 20 deg. and 40 deg. apex angle at subsonic and supersonic speeds, using a Mach-Zehnder interferometer with appendix: sensitivity and accuracy of the interference method applied to pressure measurements

D. C. Pack; E. Groth (1946)

An investigation has been made in the high-speed wind tunnel A 7 of the Luftfahrtforschungsanstalt. Brunswick, of the flow past finite wedges of 20 deg. and 40 deg. apex angle at both subsonic and supersonic speeds, the ...

Oscillating wings in compressible subsonic flow

W. P. Jones (1951)

The problem of estimating flutter and stability derivatives for wings of finite span describing simple harmonic oscillations in compressible flow is considered. It is shown that the problem can be reduced to a similar one ...

The frequency response of the ordinary rotor blade, the Hiller servo-blade, and the Young-Bell stabiliser

G. J. Sissingh (1950)

The present report deals with the frequency response of pivoted gyratory systems, and in particular, with the response of the ordinary rotor blade, the Hiller servo-blade, and the Young-Bell stabiliser to sinusoidal ...

Velocity distribution on thin tapered wings with fore-and-aft symmetry and spanwise constant thickness ratio at zero incidence

S. Neumark; J. Collingbourne (1951)

This report is a continuation of three earlier ones by the present authors (1947-9) and contains a theoretical investigation of subsonic flow past thin tapered unswept wings (of full or cropped-rhombus plan form), at zero ...

Optical considerations and limitations of the Schlieren method

G. S. Speak; D. J. Walters (1950)

The elementary principles of the schlieren method are first described, with reference to an ideal basic system. Various developments from this basic system are then considered with particular reference to their advantages ...

The rolling power of an elastic swept wing

E. G. Broadbent (1950)

An iterative method of solution is given for the problem of loss in rolling power due to wing deformation. The method is applicable at subsonic or supersonic speeds, and compressibility effects are allowed for, provided ...

Tunnel-wall effect on an aerofoil at subsonic speeds

A. Thom; Laura Klanfer (1951)

This is a detailed study of the effect of the presence of walls on the flow past a symmetrical aerofoil at zero incidence. The low-speed case is considered first, followed by solutions at a Mach number of 0.7. The methods ...

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