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Neumark, S. (author)
The note suggests a rapid and efficient method of computing the roots of an arbitrary cubic equation with real coefficients, by using specially computed 5-figure tables, and also a method of factorizing an arbitrary quartic equation by an appropriate use of a resolvent cubic. A few examples illustrate both methods.
report 1962
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Squire, L.C. (author)
Measurements have been made of the lift and pitching moments of one plane and three cambered slender ogee wings (p = 0·45, ST/co = 0·208) at four supersonic Mach numbers up to 2·0. The plane wing and one of the cambered wings are smaller scale versions of models tested previously, and provide a link between tests in the 3 ft x 3 ft and 8 ft x 8...
report 1962
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Purkiss, R.P. (author)
A description is given of a punched paper tape output designed to fit in with en existing data system as an alternative to recording on punched cards. The existing data system is briefly described with an indication of the minor modifications necessary to incorporate the new facility.
report 1962
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Woodley, J.G. (author)
This Note describes transient wall temperature measurements made on a 15° total-angle cone at zero incidence in an airstream of Mach number 6·8. The skin of the model was sufficiently thin to allow it to reach zero heat transfer conditions within a running time of one minute. In order to reduce effects of longitudinal heat conduction during a...
report 1962
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Woods, B.A. (author)
A linearized treatment is given of boundary-layer effects on the reflection of a shock wave at the closed end of a tube. The velocity af the reflected shock and the pressure behind it are perturbed (a) by the flow non-uniformity caused in the initial shock tube flow by boundary layer growth and shock attenuation, and (b) by the effect of the...
report 1962
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Portnoy, H. (author)
The method of generalised conical flows has previousiy been developed subject to the condition that the upwash divided by the streamwise co-ordinate to the power K, where K is the order of the conical flow, must have vanishing (K 1)th derivative with respect to the conical co-ordinate. In the present note this restriction is removed. The results...
report 1962
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Mabey, D.G. (author)
A transonic similarity correlation of the terminal shock jump measured on some NACA 16-series and RAE 104 aerofoils is illustrated.
report 1962
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Edwards, J.B.W. (author)
The zero-lift drag of a slender-wing model has been measured using the free-flight technique and the wing wave drag has been deduced by subtracting the non-wave-drag components. The results are presented without correction for the drag increment caused by the transition strip and show a smooth variation of the wave drag factor Ko with Mach...
report 1962
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Wells, E.W. (author)
A number of flights have been made at low altitude over three routes in the U.K. The routes were in Sussex, East Anglia and Wales. Measurements made with a counting accelerometer have been analysed to investigate the effect of variation in terrain and meteorologioal conditions on the intensity of turbulence. A comparison has also been made...
report 1962
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Lighthill, M.J. (author)
This lecture, delivered on 8th November 1962 to the Club der Luftfahrt in Bonn, is an account of blind landing prepared with the aim of interesting a non-specialist audience in this and other British developments.
report 1962
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Cox, S.G. (author)
This note describes a type of gas valve which was supplied for use on the R.A.E. 6 inch shock tube for use at pressures up to 15,000 p.s.i. and the development and acceptance tests that were carried out on it before it could be accepted as suitable for the required duty.
report 1962
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Sobey, A.J. (author)
A practical procedure for the investigation of the state of stress around an arbitrary doubly-symmetric hole in infinite elastic sheets in tension and shear is presented. The associated problem of conformally mapping an arbitrary region on to the unit-circle is solved using an iterative technique.
report 1962
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Carpenter, W.G.D. (author), Sewell, J.H. (author)
Thermal emissivities of some metallic surfaces, of various metallic surface treatments and of non-metallic (paint) finishes have been measured over the temperature range 70°C to 250°C. The emissivities of polished and vapour-blasted metallic surfaces were found to be low, whilst anodised aluminium gave high values. All the paint finishes tested...
report 1962
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Zandbergen, P.J. (author)
doctoral thesis 1962
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Holtrop, J.F. (author)
doctoral thesis 1962
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Van Hest, J.A.M. (author)
doctoral thesis 1962
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Idziak, E.S. (author)
doctoral thesis 1962
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Van Buren, M. (author)
Document(en) uit de collectie Chemische Procestechnologie
report 1962
document
Viersma, T.J. (author)
public lecture 1962
document
report 1962
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