bluuebunny/crossref_metadata_2025 huggingface dataset:
The Pilot's Problems
Authors: Prowse Captain B. O.
Published: July 2016

When considering the problems of take-off and landing from the pilot's point of view, the most important fact to remember is that he is a human being. This drawback immediately limits his capabilities in the operation of an aeroplane because the control of a pilot's actions is through the computer we call the brain. This computer, although extremely efficient in almost all functions, has nevertheless serious limitations when it comes, first, to speed of computation, and secondly, the number of functions it can compute at one time.

Until now the speed of operation of aircraft has been compatible with the speed of computation of the human brain that is governing the pilot's reactions. Also the size and complexity of the aircraft and the operation have been compatible with the number of functions the brain can compute at one time
The Human Engineering Approach
Authors: Coombes L. P.
Published: July 2016

I claim to have no expert knowledge on landing aids, but the Aeronautical Research Laboratories in Australia have done some work in this field. We were invited, or encouraged, to take up this branch of work by a Meeting of the Commonwealth Advisory Aeronautical Research Council in Australia in 1955, when the difficulties of the landing phase and the need for some form of aid for the pilot were emphasised.

I need say nothing about the difficulties of the pilot: they have already been amply emphasised. An early example of operational research in this field was an investigation made by Professor Collar in 1941 on the problem of the dark night take-off, when the pilot tends to mistake forward acceleration for a climb in the absence of sufficient external visual cues.
Operational Problems in South Africa: The Regulatory Authority's Approach
Authors: Roux Dr. A. J. A.
Published: July 2016

Before any aircraft type is granted a certificate of airworthiness its performance characteristics are accurately determined and, for large aircraft at least, scheduled in an approved flight manual. Superimposed on these data are certain basic performance criteria which usually limit the operational weight with altitude and temperature, and these limitations apply under all operating conditions.

In order to ensure a satisfactory level of safety for daily operation under varying conditions it is necessary to apply an operations code which takes into account other parameters such as :

(a) runway surface, gradient and length,

(b) obstructions in the take-off and landing flight paths,

(c) obstructions en route.
On the Aerodynamic Design of Slender Wings
Authors: Maskell E. C. , Weber J.
Published: July 2016

—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.
The Coefficient of Contraction in the Flow Through Perforated Plates
Authors: Morgan P. G.
Published: July 2016

The Coefficient of contraction of a jet of fluid flowing through an orifice has been widely studied in the field of hydraulics, using a jet of water discharging through an orifice into the atmosphere and measuring the area of the jet at the vena contracta. the coefficient of contraction cr is then defined as:
PRINCIPLE AND POLICY IN PRIVATE LAW REASONING
Authors: Plunkett James
Published: July 2016

Under 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.
SILENCE IS GOLDEN: IMPLIED TERMS IN THE SUPREME COURT
Authors: O'Sullivan Janet
Published: July 2016

LIKE the interpretation of the express words in a contract, the implication of terms in fact is traditionally explained as a way of the court giving effect to what the parties intended, judged objectively. So the two processes have something in common at a high level of generality. Much more controversial is the suggestion, made by Lord Hoffmann giving the opinion of the Privy Council in Attorney General of Belize v Belize Telecom Ltd. [2009] 1 W.L.R. 1988, that the process of implying terms is merely an aspect of interpretation: “There is only one question: is that what the instrument, read as a whole against the relevant background, would reasonably be understood to mean?” This analysis, which generated intense academic debate, had not been considered by the Supreme Court until the recent decision in Marks and Spencer plc v BNP Paribas Securities Services Trust Company (Jersey) Ltd. [2015] UKSC 72.
CERTAINTY IN VICARIOUS LIABILITY: A QUEST FOR A CHIMAERA?
Authors: Morgan Phillip
Published: July 2016

COX v Ministry of Justice [2016] UKSC 10; [2016] 2 W.L.R. 806, and Mohamud v Wm Morrison Supermarkets plc. [2016] UKSC 11; [2016] 2 W.L.R. 821 expand the reach of vicarious liability. In Various Claimants v Institute of the Brothers of the Christian Schools [2012] UKSC 56; [2013] 2 A.C. 1 (“CCWS”), Lord Phillips had declared vicarious liability “is on the move”. Lord Reed stated in Cox “it has not yet come to a stop”.
DIRECTORS' DUTIES AND IMPROPER PURPOSES
Authors: Worthington Sarah
Published: July 2016

IN Eclairs Group Ltd. v JKX Oil & Gas plc.; Glengary Overseas Ltd. v JKX Oil & Gas plc. [2015] UKSC 71, the Supreme Court had a rare opportunity to analyse the rules on directors' exercise of power for improper purposes, and to do so in a context which raised more subtleties than earlier authorities.
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

Background

Psychological 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.

Method

Forty-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’.

Results

CD 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.

Conclusions

Evidence 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

Background

Tests 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.

Method

Wechsler 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.

Results

WTAR 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.

Conclusions

MMSE, 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

In 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.
Historical and General Introduction
Authors: Vessey H. F.
Published: July 2016

This is the first meeting at which it has been possible to talk openly about transonic tunnels with ventilated working sections. Many already knew that a large number of tunnels, particularly in the U.S.A. and this country are being built or modified with slotted or perforated working sections. Up to quite recently, however, security considerations have shrouded this work but it is now possible to draw the curtain.
Some Aspects of Transonic Tunnel Operation in Industry
Authors: Roe F. E.
Published: July 2016

Early in 1950 it was decided to modify experimentally the original jet–driven tunnel of the English Electric Company—Aircraft Division, from a subsonic to a transonic tunnel. This was inspired by the work of Ward and Wright at Langley Field. As little was known then of the pressure ratio to operate a transonic working section, the working section area was reduced from a 3 8 square foot subsonic section which could be choked, to one square foot. The working section and diffuser for this modification were quickly manufactured from wood. In addition to the new working section and diffuser, a steel fairing was added to reduce the cross sectional area of the mixing length and so match the smaller induced mass flow.
The First Lanchester Memorial Lecture
Authors: Von Kármán Theodore
Published: July 2016

I Consider it a great honour to be invited to deliver the First Lanchester Memorial Lecture, which, according to the instruction received from the Secretary of the Royal Aeronautical Society, should deal with Lanchester's personality and achievements. It is also a great pleasure for me to recall my personal contacts with this great man. On the other hand, I am not quite sure whether the decision of the Council, choosing me as the first Lanchester Lecturer, was really a wise one, since I am not in the best position to present a full biographical sketch of Lanchester. Somebody more familiar with Lanchester's automobile work, as, for example, Sir Harry Ricardo, would be more able to present a full picture of Lanchester's achievements. I must, therefore, restrict myself essentially to the treatment of Lanchester's contributions to the sciences of Aerodynamics, Flight Mechanics and Operational Analysis.
Flight Development of the Avro CF-100 Mark 5 Aircraft
Authors: Whittley D. C.
Published: July 2016

Improvements 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.
Ram-Jets
Authors: Probert R. P.
Published: July 2016

The present time, when the prospect of high speed flight often seems to recede, not to approach, may well be a good occasion to review the ram-jet, an engine whose main use is at high flight speed. We owe the succinct name “ ram-jet” to the Americans and the original idea to the French. But despite the admirable efforts abroad this paper is most concerned with British ideas, especially and naturally with those conceived and prosecuted at the National Gas Turbine Establishment. At the outset it is appropriate to acknowledge all the separate personal contributions to the subject of this paper and the assistance of my colleagues in preparing some of the information presented.
The Future of Aeronautical Research
Authors: Duncan W. J.
Published: July 2016

We are now, I believe, at a time of crisis in aeronautics and in Great Britain the sense of crisis is made more acute on account of the issue by the Government of the White Paper on Defence for 1957. This paper announces vitally important changes of Government policy which are intimately concerned with aeronautics. For example, the policy is to make the English Electric P.l Supersonic Fighter the last of the manned fighter aircraft in Britain and to concentrate effort in defensive aircraft upon the unmanned guided weapon.
The Effect of Shock Waves on the Isentropic Efficiency of Convergent— Divergent Nozzles
Authors: Martin B. W. , Bayley F. J.
Published: July 2016

Now a Days, the phenomenon is well known of the plane normal shock waves set up in the divergent section of a convergent-divergent nozzle, and the oblique shocks which occur in the resultant jet downstream of the nozzle exit when operating under overall pressure ratios less than the design value. Stodola was among the first to demonstrate experimentally the effect on the flow within the nozzle of increasing the back pressure above the design value, and work by Schmidt, Martin) and others, has been concerned with the theoretical changes in pressure, temperature, density and Mach number across a normal shock wave whose position varies along the nozzle axis. The effect of working substance on these changes, which is taken into account by the ratio of specific heats, has also been investigated.
Fatigue of a Nut and Bolt
Authors: Walker P. B.
Published: July 2016

Tension bolts are widely used in engines, in machinery of various kinds, and in structures. They have unique advantages in their contribution to ease of assembly and dismantling. They also give a comparatively rigid and compact joint, and from the standpoint of static strength are extremely efficient. Unfortunately they have not got a good reputation from the standpoint of fatigue. Some designers go to considerable trouble to avoid them. Others accept their limitations and ensure safety by care in detail design and by adopting conservative figures for design stresses. Where necessary, a limitation is placed on working life, at the expiration of which the nut and bolt are replaced by new ones.
Guided Flight Trials
Authors: Boswell R. W. M.
Published: July 2016

Early in 1946, when work on guided weapons had only just begun in the United Kingdom, it became clear that there was a future need for a long Range, preferably over land, for the testing and development of guided weapons. Such a Range could not be located in the British Isles, and a survey throughout the British Commonwealth indicated that Australia was most likely to provide a suitable site. Therefore, a party of Ministry of Supply and Ministry of Aircraft Production personnel under the leadership of Lieut. General (now Sir John) Evetts carried out a preliminary survey in 1946, selected a site in South Australia which appeared most suitable and submitted a detailed report to the Ministry of Supply.
The Helicopter as an Agricultural Tool
Authors: Little E. C. S.
Published: July 2016

The aviation industry has not yet given much attention to the development of rotary winged machines as specialist agricultural tools which would help to make farming easier, more efficient and more productive. The emphasis is, and naturally has been, on the development of the immediately bigger markets for military aircraft. It is understandable, if unfortunate, that the farmer has to wait his turn well down in the queue of various armed forces specialists. He is waiting for aviation to turn the focus, some day, of its technical knowledge and research resources onto the way that the versatility, manoeuvrability and usefulness of the helicopter can be used to grow more food, timber, wool and other natural products.
Temperature Inequalities in the Electrolytic Tank
Authors: Platt A. , Norbury J. F.
Published: July 2016

Accurate representation of a model field in an electrolytic tank requires, among other things, that the electrical conductivity of the liquid should be everywhere constant. Einstein and Sander and Yates have discussed the importance of other possible inaccuracies, and have shown that by correct probe design, circuit design and choice of electrode materials, these may be made very small. This note describes very briefly some experiments, carried out in two shallow electrolytic tanks, which demonstrate that the principal error can be that introduced by variations of conductivity produced by non-uniformity of temperature distribution in the electrolyte. The point is of particular importance since the results also showed that the mechanical design of the tank can have a vital bearing on the achievement of uniform temperature.
The Application of the Theory of Stability in Structural Design
Authors: Cox H. L.
Published: July 2016

It is never satisfactory to design a structure piecemeal. The whole construction ought to be considered as one unit and designed from the outset to meet each of the several loading actions to which it may be subjected. Part structures designed for one principal loading system and later modified to accord with other part structures or to meet other loading requirements, will seldom prove efficient. Moreover a structure designed from the outset to meet alternative loading cases is necessarily better integrated than a structure designed primarily for one loading case and later modified to meet another.
Semi-Empirical Methods of Estimating Forces on Bodies at Supersonic Speeds
Authors: Phythian J. E. , R. L. Dommett
Published: July 2016

Semi-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.
A Tensile Strut Testing Machine
Authors: Fessler H.
Published: July 2016

Slender Struts are usually tested with pin joints at both ends, because this is the theoretical condition which is most readily achieved (or closely approximated to) in practice. In conventional testing machines this results in a compression column with two pin joints. The instability of this column makes the accurate alignment of the loading members important, and reliable testing becomes correspondingly difficult.
A Note on the Calculation of Torsional Natural Frequencies of Branch Systems
Authors: Gilbert Arthur C.
Published: July 2016

An Adoption of matrix techniques is proposed as a method for the solution of torsional natural frequencies in a branch or geared shaft system. Both fundamental and higher mode shapes and frequencies are produced by a comparatively rapid and straightforward technique. The method is illustrated by a numerical example of a coupled turbine and reciprocating engine system driving a common propeller.
Note on the Solution of Non-Linear Simultaneous Equations by Successive Approximations
Authors: Goodey W. J.
Published: July 2016

The Calculation of the roots of an algebraic or transcendental equation in a single unknown is a problem of frequent occurrence. For a real root the usual procedure is to obtain a first approximation to the required quantity, graphically or otherwise, and to improve this approximation by successive applications of the Newton-Raphson process. The extension of this process to the improvement of an approximate solution of a set of non-linear simultaneous equations in n unknowns is fairly obvious, but it does not seem to have received much attention in text books, although the case of two unknowns is dealt with in Ref. 2.
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.
Complexity and Progress in Transport Aircraft
Authors: Rowe N. E.
Published: July 2016

During my five years from July 1929 at Weybridge the amount that was done was amazing, although the technical and design staffs were microscopic by present-day standards. The types included Vimy, Virginia, Victoria, B.19/27 Night Bomber—all of these were twin-engined—Type 163, 4-engined Night Bomber, a P.V. with tandem engines; Vespa, Vildebeeste Torpedo Bomber and other roles, C.O.W. Gun Fighter, G.4/31 Reconnaissance Bomber (2 versions)—all of these were single engined military machines; Viastra, passenger carrier, Vellore and Vellox Freighters—twin-engined civil aircraft, although Viastra first flew with three engines. All were biplanes with the exception of the C.O.W. Gun Fighter, the Viastra and the second prototype G.4/31 which were monoplanes. Incidentally, the G.4/31 was the first example of geodetic construction, the fuselage being so constructed. My recollection is that Mr. Wallis was responsible for the structural design of this aircraft which had an unusually large aspect ratio. It became the Wellesley, had a most honourable career in the R.A.F. and of course held the world's long distance record for many years.
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.
A Note on the Effect of Surface Finish on the Thrust of a Supersonic Conical Nozzle
Authors: Rowe P. N.
Published: July 2016

The Propelling Nozzles tested are turned from brass and the interior surface finish shows a centre line average of about 15 micro inches when examined on a Taylor Hobson machine. This is fairly rough compared with the estimated boundary layer thickness and it was required to know whether this in fact affected the thrust. The thrust of a nozzle manufactured by the usual process was measured before and after a polishing process. An improvement of one half per cent was recorded.
Annular Flow—A Note on the Turbulent Velocity Profile
Authors: Barrow Henry
Published: July 2016

The Important characteristics of the turbulent velocity profile of a plain concentric annulus and some of the methods of correlating the velocity distribution are briefly reviewed. The average velocities in an annular section are examined and some experimental data is correlated by a modified power law.
The Fourteenth British Commonwealth Lecture
Authors: Floyd J. C.
Published: July 2016

In preparing this lecture I was conscious of the fact that there were many phases of the development of a modern fighter which I had not covered, and which would possibly be of greater interest to the specialists on that particular subject than those that I did include. To them I offer my apologies, however, this lecture is not intended to be a handbook or reference on the design of all-weather fighter aircraft, but was prepared more or less as a chronicle of the main events leading up to the current development flying of Canada's newest defence weapon system, the supersonic all-weather CF-105, or Avro Arrow, and its associated equipment and environment (Fig. 1).
Measurements of Skin Friction in a Plane Turbulent Wall Jet
Authors: Sigalla A.
Published: July 2016

Results 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.
A Simplified Numerical Analysis
Authors: Maley C. E.
Published: July 2016

Liaison between the engineering and computing sections of an aircraft company suffers when the engineer feels he is “losing control” of his own problems. This situation is typically due, not to distrust of the calculating engine, but to variance in the numerical methods favoured by the engineer and the engine programmer.
The Mechanism and Application of Effusion Cooling
Authors: Grootenhuis P.
Published: July 2016

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

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.
A Theoretical Treatment of the Flutter of a Wing with a Localised Mass
Authors: Gaukroger D. R.
Published: July 2016

Flutter calculations were made on a fixed root model wing carrying a localised mass. Modes were calculated for the wing for certain conditions of restraint at the localised mass position, the choice of modes being based on observation of the behaviour of wind tunnel models under fluttering conditions. The general agreement between the calculations and experimental results was good and justified the extension of the calculations to conditions of localised mass loading that were not covered by experiment. The extended calculations show that there is an optimum spanwise position for a localised mass from the flutter point of view and, that this optimum position is related to the nodal line position in the overtone torsion mode of the bare wing. For values of localised mass parameters likely to occur in practice, flutter speeds can be estimated from calculations in a very limited number of modes, the choice of modes depending on the localised mass loading.
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.
Magnetogasdynamies and its possible Aeronautical Applications
Authors: Shercliff J. A.
Published: July 2016

Professor Lighthill's paper has discussed the dissociative behaviour of air at the high temperatures produced when it is compressed in a shock or heated by friction in a boundary layer under hypersonic flight conditions. Just as molecules may dissociate into atoms, so may these molecules and atoms split further into charged ions and electrons. The equilibrium state of this ionisation process is amenable to the same thermodynamical or statistical-mechanical treatment as in the case of dissociation, the Law of Mass Action in this context being referred to as the Saha equation. Consider the simplest case where a monatomic gas is singly ionised, a fraction α of the atoms having lost one electron, so becoming singly charged positive ions.
Aerodynamic Problems of Manned Space Vehicles
Authors: Nonweiler T. R. F.
Published: July 2016

The intention of this paper is to point out certain aerodynamic problems that may be of future interest, by trying to argue in general terms about their possible context. Perhaps the most distinctive feature of any project analysis of a vehicle designed to carry a man into an orbit in space and return him safely to the ground, is the need to limit the accelerations and retardations of his passage, and the temperature of his environment. There are of course innumerable other considerations which have to do with his comfort and safety, but it is his inability to withstand excessive heat or high g which distinguishes man from more rugged but less versatile instruments.
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 by

it 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

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:
Problems of Interplanetary Navigation and Atmospheric Re-Entry
Authors: Nonweiler T. R. F.
Published: July 2016

In this lecture i want to survey some of the problems of the aerodynamics of re-entry, as they affect either purely earth-bound or space vehicles; and in particular, as they are affected by the trajectory the vehicles are designed to follow, or may find themselves upon due to some error of navigation. This is a self-set task and an ambitious one: but in truth it is an artful one, as it provides an excuse for me to leave the discussion of problems at a stage where their difficulties begin to defeat me.
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.
The Development and Flight Testing of Helicopters
Authors: Sarsted G. J. , Coles A. V.
Published: July 2016

The successful development of a helicopter and its introduction into service may be influenced by several factors but a well co-ordinated development programme is by far the most important. A practical and realistic balance between representative ground tests and the subsequent flight proving is essential if the project is to be completed within a reasonable budget and time scale. The two parts of this paper cover these phases and aim to show how they are related in a particular development programme. The use of major fully representative ground rigs is discussed in relation to pre-flight functioning and fatigue life assessment; this is followed by the initial flight trials and finally the structural and performance clearance of the helicopter over its full design envelope. Although the tests and techniques described are generally applicable, the examples quoted relate to the Bristol Type 192, tandem rotor helicopter. The opinions expressed are personal and do not necessarily represent those of the Bristol Aircraft Limited.
Deck Landing
Authors: Shaw A. I. R.
Published: July 2016

Forty-two years ago—on 2nd August 1917—the first deck landing on a ship under way was made. A special platform had been constructed on the battle cruiser Furious, and it was on this prototype flight deck that Squadron Commander E. H. Dunning made the first successful aeroplane landing aboard ship. On touching down, his aircraft—a Sopwith Pup—was restrained manually by the (presumably) willing hands of a large number of officers and men. Two days later a second attempt ended in disaster. But from this beginning, like so many initial steps forward in aviation, a sad one, grew the Fleet Air Arm as we know it today.
A Note on the Induced Drag of Jet-Flapped Wings
Authors: Korbacher G. K. , Sridhar K.
Published: July 2016

The main purpose of this note is to explain the apparent discrepancy which arises when the change in effective aspect ratio due to blowing, as predicted by the theoretically derived expression for the induced drag coefficient, is compared with what one intuitively expects from the general flow picture. If the jet sheet is considered as a chordwise extension of the wing (mechanical flap analogy), the general flow picture suggests that the effective aspect ratio of a wing without blowing is reduced by blowing. Maskell and Spence's relation for the induced drag coefficient, however, indicates that the effect of jet blowing is to increase the effective aspect ratio.