bluuebunny/crossref_metadata_2025_split huggingface dataset:
On the Aerodynamic Design of Slender Wings
Authors: Maskell E. C. , Weber J. 
Published: July 2016

Summary:—Since flow separation occurs readily from a highly swept leading edge, but gives rise in general to a steady flow, it is proposed that the rational approach to the aerodynamic design of slender wings is to attempt to control, rather than to suppress, these separations. This leads to the suggestion that the leading edges should be sharp, and that the wing should be shaped so as to make them attachment lines at one attitude (the design attitude) at which classical wing theory can be applied. It is argued, further, that if the leading edge separations are to develop regularly with change of attitude of the wing, separation must occur only from the trailing edge at the design attitude; and the velocity field favourable to boundary layer development without separation forward of the trailing edge is discussed. Subject to the restrictions thus imposed on the design, low drag is sought at the design attitude. This leads to the consideration of a particular class of doubly curved mean surfaces satisfying the leading edge condition, onto which thickness distributions are superposed so as to provide favourable velocity fields together with low drag. A number of examples are considered, using slender thin wing theory for flexibility, to illustrate the manner in which plan form and thickness distributions affect the pressure distribution, and to indicate the relatively high lift/drag ratios which seem feasible. Some consideration is given to the limitations of the theory used and to the further developments which seem desirable.
PRINCIPLE AND POLICY IN PRIVATE LAW REASONING
Authors: Plunkett James 
Published: July 2016

AbstractUnder the present law, policy-based reasoning plays a major role in the judicial determination of private law disputes. The propriety of this type of reasoning, however, has been the subject of much debate. Whilst many argue that there is nothing objectionable about using policy-based reasoning, others, particularly those who believe in a rights and/or corrective justice-based view of private law, argue that policy should play no role in the determination of private law disputes, and that courts should instead rely on what they call “principle”. This article will examine both sides of the debate, initially exploring what is actually meant by “principle” and “policy”, and then providing an overview of the primary arguments relied on in favour of both a policy- and principle-based approach to resolving private law disputes. Finally, a compromise between the two approaches, the so-called “pluralist” approach, will be examined.
Life events and escape in conversion disorder
Authors: Nicholson T. R. , Aybek S. , Craig T. , Harris T. , Wojcik W. , David A. S. , Kanaan R. A 
Published: July 2016

BackgroundPsychological models of conversion disorder (CD) traditionally assume that psychosocial stressors are identifiable around symptom onset. In the face of limited supportive evidence such models are being challenged.MethodForty-three motor CD patients, 28 depression patients and 28 healthy controls were assessed using the Life Events and Difficulties Schedule in the year before symptom onset. A novel ‘escape’ rating for events was developed to test the Freudian theory that physical symptoms of CD could provide escape from stressors, a form of ‘secondary gain’.ResultsCD patients had significantly more severe life events and ‘escape’ events than controls. In the month before symptom onset at least one severe event was identified in 56% of CD patients – significantly more than 21% of depression patients [odds ratio (OR) 4.63, 95% confidence interval (CI) 1.56–13.70] and healthy controls (OR 5.81, 95% CI 1.86–18.2). In the same time period 53% of CD patients had at least one ‘high escape’ event – again significantly higher than 14% in depression patients (OR 6.90, 95% CI 2.05–23.6) and 0% in healthy controls. Previous sexual abuse was more commonly reported in CD than controls, and in one third of female patients was contextually relevant to life events at symptom onset. The majority (88%) of life events of potential aetiological relevance were not identified by routine clinical assessments. Nine per cent of CD patients had no identifiable severe life events.ConclusionsEvidence was found supporting the psychological model of CD, the Freudian notion of escape and the potential aetiological relevance of childhood traumas in some patients. Uncovering stressors of potential aetiological relevance requires thorough psychosocial evaluation.
Why is Mini-Mental state examination performance correlated with estimated premorbid cognitive ability?
Authors: Dykiert D. , Der G. , Starr J. M. , Deary I. J. 
Published: July 2016

BackgroundTests requiring the pronunciation of irregular words are used to estimate premorbid cognitive ability in patients with clinical diagnoses, and prior cognitive ability in normal ageing. However, scores on these word-reading tests correlate with scores on the Mini-Mental State Examination (MMSE), a widely used screening test for possible cognitive pathology. This study aimed to test whether the word-reading tests’ correlations with MMSE scores in healthy older people are explained by childhood IQ or education.MethodWechsler Test of Adult Reading (WTAR), National Adult Reading Test (NART), MMSE scores and information about education were obtained from 1024 70-year-olds, for whom childhood intelligence test scores were available.ResultsWTAR and NART were positively correlated with the MMSE (r ≈ 0.40, p < 0.001). The shared variance of WTAR and NART with MMSE was significantly attenuated by ~70% after controlling for childhood intelligence test scores. Education explained little additional variance in the association between the reading tests and the MMSE.ConclusionsMMSE, which is often used to index cognitive impairment, is associated with prior cognitive ability. MMSE score is related to scores on WTAR and NART largely due to their shared association with prior ability. Obtained MMSE scores should be interpreted in the context of prior ability (or WTAR/NART score as its proxy).
Dogorchien? Translation equivalents in the receptive and expressive vocabularies of young French–English bilinguals
Authors: LEGACY JACQUELINE , REIDER JESSICA , CRIVELLO CRISTINA , KUZYK OLIVIA , FRIEND MARGARET , ZESIGER PASCAL , POULIN-DUBOIS DIANE 
Published: July 2016

AbstractIn order to address gaps in the literature surrounding the acquisition of translation equivalents (TEs) in young bilinguals, two experiments were conducted. In Experiment 1, TEs were measured in the expressive vocabularies of thirty-four French–English bilinguals at 1;4, 1;10, and 2;6 using the MacArthur Bates CDI. Children's acquisition of TEs occurred gradually, with more balanced ratios of exposure and vocabulary associated with larger proportions of TEs at each wave. Experiment 2 compared a direct measure of TE comprehension with parent report of the same set of words. Results showed that parents may over-report children's TE comprehension, as our sample of two-year-old French–English bilinguals (n= 20) comprehended fewer TEs on a direct measure of receptive vocabulary than parents reported on the vocabulary checklist. The present study provides an original contribution to the literature on bilingual vocabulary development by employing both a longitudinal design and a direct measure of TE comprehension.
Flight Development of the Avro CF-100 Mark 5 Aircraft
Authors: Whittley D. C. 
Published: July 2016

SummaryImprovements made to the aerodynamic characteristics of the wing of the Avro CF-100 Mark 5 aircraft are discussed. Modifications to the wing included increase in aspect ratio, addition of vortex generators, and deflection of trailing edge plain flaps. The effect of flap deflection and addition of vortex generators on the aerodynamic characteristics of the wing are shown to be closely associated with interaction of the upper surface shock wave with the boundary layer. Performance gains were demonstrated at high subsonic speeds at high altitudes. Vortex generators improved the buffet boundary, whereas flap deflection both increased aircraft ceiling and improved buffet boundary.
Semi-Empirical Methods of Estimating Forces on Bodies at Supersonic Speeds
Authors: Phythian J. E. , R. L. Dommett  
Published: July 2016

SummarySemi-empirical methods are described for obtaining the normal forces and centre of pressure positions of isolated cone-cylinders and ogive cylinders with and without boat tails at supersonic speeds. The data for normal force slope and centre of pressure at zero incidence is, in general, accurate to better than 10 per cent and half calibre respectively. The data for high incidence must be considered speculative although reasonable agreement has been found with the very limited experimental data available.
Gas Turbines For Helicopters
Authors: Morley A. W. 
Published: July 2016

Rapid developments in the use of the helicopter were made in the Korean War. These were taking place at the time when there was considerable urge to introduce the gas turbine engine into the civil aircraft market. It was also a time when much effort was being expended on various forms of reaction propulsion, mostly for missiles. A number of new helicopter projects were started, taking advantage of the new knowledge in propulsion engineering; some utilised new gas turbine designs and others various forms of tip jet reaction. Liquid fuel rockets, ram-jets, pulse-jets and air pressure jets were tried. However, the main line of development continued to be the gradual improvement of direct mechanical drive.Since Korea the natural trend has been first to convert existing helicopters to turbine engines. When new helicopters were designed wisdom dictated mechanical drive pending the gathering of sufficient experience with other forms of rotor power, and so far the accumulated knowledge of the mechanical drive has proved of greater value to helicopter progress than the potential advantages offered by the alternative engine forms.
Problems in the Development of a Guided Weapon
Authors: Clemow J. 
Published: July 2016

The subject of this paper is a wide one. Guided weapon development problems in one form or another have been my daily concern for more than ten years now and I must be highly selective in the brief time at my disposal on this occasion.The object of guided missile development is to produce efficient weapons of war, that is, weapons of destruction able to neutralise an enemy threat or destroy the enemy if he dare attack. I make this statement every time I talk on guided weapons, and I make no apology for making it on this occasion. We must not at any time forget that we are concerned in the development of weapons to defend this country, that time is of the essence of the contract, that the product must stand up to storage, to usage by the Services, and must be ready for action after little warning, and so on. As in any other branch of engineering, we have to make the best use of the men, ideas, techniques and materials at our disposal in order to reach the desired objective.
Method for Providing Warning of the Onset of Buffeting, Stalling and Other Undesirable Effects of Flow Separation
Authors: Holder D. W , Pearcey H. H. 
Published: July 2016

A Method is described for providing warning of the onset of undesirable effects produced by flow separation on an aircraft wing. It is based on static pressure measurements near the trailing edge and appears to have advantages over alternative methods.Recent work has suggested that certain effects of flow separation such as buffeting, aileron buzz and undesirable changes in loading, occur when a “ bubble ” of separated flow originating at the leading edge of a wing, or at a shock wave on its surface, first becomes sufficiently large to affect the flow at the trailing edge.
Radio-Astronomy and Navigation
Authors: Cade C. M. 
Published: July 2016

The difficulties of determining latitude and longitude under adverse weather conditions, when neither the Sun nor stars can be sighted, are well-known, and the advantages of a non-visual system of position finding which could operate through clouds or fog are too obvious to require emphasis.A Radio Sextant, which detects and locks-on to 8 mm. radiation from the Sun, has already been made and tested in America with reputedly excellent results. An analysis of both the theoretical and the practical design factors is given in the present paper, together with the results of successful experiments made in Great Britain.
Measurements of Skin Friction in a Plane Turbulent Wall Jet
Authors: Sigalla A. 
Published: July 2016

SummaryResults of an experimental investigation of the distribution of skin friction along the wall of a plane turbulent wall jet are presented. The measurements show that it is possible to describe the variation of skin friction coefficient by a formula similar to the Blasius formula which is based on experimental results of turbulent pipe flow. This is simply achieved by considering the inner layer of fluid between the wall and the position where the velocity is a maximum as a boundary layer with an outer uniform free stream of velocity equal to the local maximum velocity.Other measurements of velocity distribution indicate that within the experimental range and accuracy, the velocity profiles in the jet are similar and that the rate of change of velocity and width of the jet can be expressed by simple power laws. These results are then partially compared with theory.
The Second Lanchester Memorial Lecture
Authors: Collar A. R. 
Published: July 2016

We look before and after,And pine for what is not.—Shelley.I am very appreciative of the honour that has been accorded me in being invited to deliver the Second Lanchester Memorial Lecture: appreciative, but all too conscious of my own inadequacy. This is especially true, since in the first Lecture we heard a tribute to a very great man from another such: and the prospect of following von Karman to this lectern is one to deter perhaps all but the most foolhardy. Since von Karman’s address discussed very fully the contributions of Lanchester to aeronautics, little is left for subsequent lecturers on this subject, and I have therefore chosen to speak of a problem which has been my special interest and concern throughout my professional life, namely, aeroelasticity—a field in which, as in so many others, Lanchester was a pioneer.
The Present and the Future
Authors: Banks F. R. 
Published: July 2016

I would thank you for the honour you have done me by the invitation to give this lecture.The admiration I have always had for the engineer founder of this famous Derby firm, and the affection for the firm itself from many contacts over the years, both as an itinerant fuel development engineer and, later, as an official in a Government Department, makes this a very pleasant occasion for me.
The Mechanism and Application of Effusion Cooling
Authors: Grootenhuis P. 
Published: July 2016

Summary:Effusion cooling consists in forcing a gas under pressure through a porous material thereby absorbing heat from the material and forming a heat insulating layer on the exposed surface. The internal heat transfer between the porous material and coolant is considered and the heat transfer coefficient obtained from experiment. An approximate analysis for the heat insulating effect based on a heat balance method is derived in detail and applied to experiments with porous plugs set into the side of a duct carrying hot gases, and to porcras cylinders swept by hot gases. It has been found that this analysis applies reasonably accurately to the results of these experiments and of most of the published data. The manufacture of porous materials is discussed briefly and a representative list of commercially available materials is included. The application of effusion and sweat cooling to the blading and combustion chamber linings for gas turbines, rocket motors and the outside skin of flying vehicles is considered.
Residual Stresses Resulting from the Forming of High Strength Aluminium Alloys
Authors: Hawkes G. A. 
Published: July 2016

Summary:An X-ray back reflection technique has been used to measure the surface residual stresses resulting from the cold and hot forming of certain high strength aluminium alloys. The alloys examined were to specifications DTD 683, DTD 687 and B.S.S. L65, and the residual stresses have been related to the residual strain in bending of these alloys. The results show that, apart from the degree of straining, the residual stresses are affected by the heat treatment (cold or hot quench) and the amount (if any) of controlled stretching that the alloy has had between solution treatment and precipitation.
Freighters—A General Survey
Authors: Keen E. D. 
Published: July 2016

The 32nd Main Lecture of the Society to be given at a Branch Centre, “ Freighters—A General Survey “ by Mr. E. D. Keen, B.Sc., A.F.I.A.S., F.R.Ae.S., was held under the auspices of the Birmingham Branch on 4th December 1958.MR. F. F. CROCOMBE, F.R.Ae.S., President of the Birmingham Branch, opened the meeting by reminding those present that this was the second Main lecture to be held at the Birmingham Branch since its formation in 1944. The Branch had never been a large one and now numbered about 100 members drawn from local aviation enthusiasts and representatives of aircraft equipment and motor industry firms in the area. There was some longer-range support from Coventry and Wolverhampton but little from their own Birmingham University. Mr. Crocombe then welcomed the visitors, particularly the strong representation from Armstrong Whitworth and Blackburn and General Aircraft Ltd. He welcomed especially the President of the Society, Sir Arnold Hall, M.A., F.R.S., F.R.Ae.S. who would preside over the rest of the proceedings.After thanking the Birmingham Branch for their hospitality, SIR ARNOLD HALL, said that the holding of Main lectures at Branches had proved to be extremely popular and the practice should certainly be continued with enthusiasm. Introducing the lecturer, the President said that Mr. Keen had been a leading member of the Branch for a long time and was at present its Vice-President. Educated at the Regent Street Polytechnic, where he took a degree of the University of London, Mr. Keen had joined Armstrong Whitworth Aircraft Ltd. in 1928 and had been with the Company ever since. He became Assistant Chief Designer in 1949 and since 1955 he had been Chief Designer. In 1955 the Society had awarded him the Simms Gold Medal for a classical paper on “ Integral Construction.” His subject now was “ Freighters,” which was a part of aeronautical engineering that he had made particularly his own, first by study and later by putting his ideas into practice.
Drone Aircraft
Authors: Conway H. G. 
Published: July 2016

It is necessary to start this paper with a disclaimer. Neither the author nor his firm have been concerned with the development of Drone aircraft for more than a few years. Others in the field have more, certainly longer, experience; the choice of the present author is probably because he has been associated with the development of the most ambitious target aircraft so far produced in Britain—the Canberra Mk. 10.The early history of work on automatic flight was discussed by Dr. G. W. H. Gardner in the 46th Wilbur Wright Memorial Lecture*. Credit is due to the Royal Aircraft Establishment for the development of more modern Drones and associated equipment, and indeed, of the whole control system which is now used for Aberporth and in Australia. Much credit is also due to the Australian authorities for the working up of the target service which they now provide at Woomera and for the development of the Jindivik target. The Fairey Aviation Company Ltd. and Flight Refuelling Ltd. have respectively been concerned with the droning of the Fairey Firefly and the Gloster Meteor aircraft which are also used as targets for British missiles.
On Similar Solutions of the Boundary Layer Equations for Air in Dissociation Equilibrium
Authors: Dommett R. L. 
Published: July 2016

Using a Stewartson transformation defined byit is straightforward to show that in the two cases for which it is possible to find similar solutions to the laminar boundary layer equations withPr≠1,Le=1, that is stagnation flowsUe∝Xand flat plate flowsUe=constant, it is not necessary to assume anything about the specific heats to derive the equations given and solved by Beckwith.
The Landing Gear of the SC.l Aircraft
Authors: Conway H. G. 
Published: July 2016

The Short SC.l is a small delta wing V.T.O. aircraft of about 7,800 lb. all-up weight. Its unusual feature is that it is provided with vertical thrusting engines to enable it to take-off and land vertically and to hover. It can also operate normally as a conventional aircraft.The nature of the aircraft introduces a number of problems in the design of the landing gear. The first of these is that all wheels must be fully castoring since a vertical landing may take place with a certain amount of drift in any direction. Another complication arises because of the possibility of landing with slight backward drift, it being necessary to move the main wheels aft when the pilot intends to make a vertical landing; if the wheels were left in the required rearward position for conventional take-off the elevator power would be inadequate to lift the nose of the aircraft. The landing gear is therefore provided with simple means for moving the wheels fore and aft by a small amount, to move the position of the main wheels in relation to the centre of gravity.
Stress Distribution Around a Central Crack in a Plate Loaded in Tension ; Effect of Finite Width of Plate
Authors: Dixon J. R. 
Published: July 2016

Summary:The purpose of the work was to investigate the effect of the finite width of plate on the elastic-stress distribution due to a central crack in a flat plate loaded in tension.The range of investigation: (i) Two-dimensional photoelastic tests were carried out on flat-plate specimens. The photoelastic specimens were geometrically similar to the 10 in. wide fatigue specimens used by Frost and Dugdale, with the central crack simulated by a slot bounded by holes of small radii, (ii) A theoretical solution of the problem was derived and compared with the present and other photoelastic results.It is shown that the effect of the crack-length/plate-width ratio on the elastic-stress concentration at the head of the crack can be expressed by the following formulae:
The Rolling Moments due to Sideslip on High Tailplanes at Subsonic and Transonic Speeds
Authors: Mabey D. G. 
Published: July 2016

Some measurements in the R.A.E. Bedford 3 ft. wind tunnel on a typical high tailplane illustrate a Mach number effect on the tailplane rolling moments due to sideslip which has been apparently overlooked previously. Fig. 1(a) shows that the increase in tailplane rolling moment due to sideslip is much larger than the increase in the fin lift curve slope a1F, Fig. 1(b). This extra increase in rolling moment is associated with the increase in the tailplane lift curve slope a1T, Fig. 1(c). In fact the rolling moment on this high tailplane varies roughly as the product of the fin and tailplane lifts, as Fig. 1(d) shows. A qualitative explanation follows.Consider the idealised high tailplane shown in Fig. 2. At zero geometric incidence and positive sideslip the fin lift will induce positive and negative incidence distributions on the starboard and port sides of the tailplane.