bluuebunny/crossref_metadata_2025 huggingface dataset:
Supersonic flow simulation for a boat-tailed heat shield
Authors: Purohit Sharad C.
Published: July 2016

For a 15° boat-tailed heat shield or payload shroud, the unsteady, compressible Navier-Stokes equations are numerically solved. For a Reynolds number of the order of one million and for four different freestream Mach numbers, the time integration is performed for 64 x 30 grid computational domain. The entire flow-field is analysed to delineate the gross dominant characteristics. It is observed that the flow in the boat-tail region is completely attached for Mach number 2·47 and beyond whereas it is separated for lower Mach numbers. A comparison between the numerical solutions and the available experimental results is provided and, for incipient flow separation conditions, an evaluation of unsteady surface pressure data is presented.
Propulsive mechanisms in animal swimming and flying locomotion
Authors: Bschorr O.
Published: July 2016

The objective of this paper is a description of animal swimming and flying locomotion in terms of wave theory. In this context various oscillatory organs of locomotion, such as flagella, fins and wings, are interpreted as waveguides capable of transmitting mechanical transverse waves. Furthermore, the Poynting concept is used, according to which every type of wave transports not only energy but also momentum. Even with no detailed knowledge of the hydro- and aerodynamic flow fields it is possible to calculate the wave power, the propulsive force, and the propulsive efficiency with the means and methods of vibrational theory alone.
Part 2. Project Management in an Aerospace Firm
Authors: Keenan J. G.
Published: July 2016

The success of a project is not measured simply by the arrival in service of a product giving its promised performance. Success means the arrival in service of a product giving its promised performance, purchased at the promised price and delivered on the promised date.

To achieve these targets with a complex aerospace product requires the effective management of a large number of people, ranging from scientists through designers, technicians, managers, accountants, typists, fitters and coppersmiths to delivery truck drivers. Their efforts must be directed, each in his proper place and time, towards a single goal. The success of the project can be influenced considerably by the type of organisation adopted for the management of this wide variety of people.
Autogyro Developments in North America
Authors: Hunt G. J.
Published: July 2016

It is my pleasure and privilege to deliver this lecture about the state of development of the autogyro in North America. I would like to deal with some of the early history of the autogyro, the progress of which had been steadily increasing up to the start of the Second World War. The introduction of the helicopter and the prospect of cheap transportation for all, tended to bring a temporary halt to autogyro construction. The last of the Cierva line of Autogiros was the C.40 which was a two-seater capable of a jump take-off by spinning up the rotor in zero pitch above the normal rpm required for flight, and using the excess kinetic energy stored in the rotor to achieve a satisfactory jump. Cierva's first autogyro experiments were conducted during 1922 using blades attached rigidly to the hub; the single rotor machines rolled over on take-off due to lift dissymmetry on the disc. Cierva also experimented with a contra-rotating rotor but this system was.unsuccessful, since the two discs did not behave in an identical manner.
Note on Transition to Turbulence in Vortex-Street Wakes
Authors: Zdravkovich M. M.
Published: July 2016

In their pioneering paper published in 1917 Nayler and Frazer showed that the process of vortex formation behind a circular cylinder can have significant three-dimensional features even when care is taken to create two-dimensional flow. Hama produced photographs which show initially straight vortex filaments becoming curved some distance behind the cylinder, with consequent three-dimensional flow. In their experiments on boundary layers Hama et al found the formation and development of “vortex loops” from such curved vortex filaments to be an essential feature preceding transition from laminar to turbulent flow, and they stated that the same would be true for transition in wakes and jets.
An Air Registration Board View
Authors: Corps S. G.
Published: July 2016

In trying to decide how best to lay out a paper for this Symposium one is conscious of a great deal of information lurking in the back of one's mind, resulting from the sort of discussion that we all have after flight, or on those frequent occasions when the weather or other exigencies delay us in our task, but I wonder just what real value would be served if too many of our contemporary problems were to be aired in public? I have no doubt that before the day is out a fair amount of soul searching will have to be done on all sides, but particularly at this time when, for one reason or another, the order books for significant British aeroplanes are far from full, I think it is a time to discuss our problems freely, but with a positive objective in sight, the furtherance of British Aviation in the world. If the symposium has brought people together who do not frequently meet “in mass” it could be that there might begin a better understanding between us, in which case our time today will have been well spent.
The Fare-Paying Passenger's View
Authors: Harris S. M.
Published: July 2016

I am More than a little nervous standing here, because I am the non-expert in a room full of experts, or if you will, a single sheep among a number of wolves.

I have been asked to represent the fare-paying passenger's point of view to a symposium of technical people, and as such I want to make it clear at the outset that what I am going to say is opinion, not entirely uninformed but certainly not expert. If out of what follows I am wrong from time to time, then I hope you will understand that it is not a deliberate attempt to make noise for noise sake, but is really representing the thoughts of the fare-paying passenger.
A Note on the Receptance Formulation of the Method of Displaced Frequencies and its Relation to the Collar-Jahn Procedure
Authors: Simpson A.
Published: July 2016

In his paper, Mahalingam describes a simple receptance approach to the displaced frequency method, and shows how (in the simple case where the added mass affects the kinetic energy of one co-ordinate only) this can be applied in the determination of corrected generalised masses. A method had been propounded previously by the present author, and this accomplished the generalised mass corrections by a procedure related to the Collar-Jahn Method for the correction of an approximate set of eigenvectors.

At first sight, the methods of refs. 1 and 2 appear very different—the first being based on dynamic flexibility relations and the second on dynamic stiffness relations. Indeed, the final forms of the equations for the corrected generalised inertias obtained from the two approaches appear radically different, and it is by no means obvious that the two methods will, in general, produce identical (or nearly identical) results.
Thermal Buckling of a Circular Plate
Authors: Mansfield E. H.
Published: July 2016

This note considers the buckling of a circular lenticular plate subjected to a temperature which varies parabolically in its plane. The novel feature in the analysis is the determination of the stiffening effect due to the prevention of deflections, but not slopes, along a diameter.
Turbine Engines in Transport Aircraft—Some Observations on Reliability and Safety in Operation
Authors: Graham J.
Published: July 2016

Any system for controlling the airworthiness of aircraft engines in service should meet the following conditions:

(a) it should be such that the incidence of in-flight shut-downs is kept to an acceptably low level;

(b) it should ensure that aircraft are not flown with engines delivering significantly lower power than that used in establishing the scheduled Flight Manual performance; and

(c) it should provide maximum protection against failures of a potentially catastrophic nature, regardless of probable incident rate.

In this paper, the foregoing principles are discussed in relation to experience with turbine engines in transport aircraft. Particular emphasis is placed on the importance of monitoring, by which is meant any procedure or device that can be used to determine engine condition in flight or on the ground. Some current trends in turbine engine overhaul policies are also reviewed briefly.
The Air Cushion Performance of a Tracked Hovercraft in a Tunnel
Authors: West A. A.
Published: July 2016

It has recently been suggested that the tracked hovercraft is a suitable means of high speed transportation. On some routes it may be necessary for the vehicle to pass through tunnels. The purpose of the present note is to determine the effects of steady tunnel operation, and in particular to find if the “piston effect” is likely to adversely affect the performance of the air cushion.
The Influence of Velocity Profile Characteristics on the Drag of Short Circular Struts Spanning Two-Dimensional Channels
Authors: Livesey J. L. , Turner J. T.
Published: July 2016

Measurements of cylinder drag in two-dimensional flow are readily available. In contrast, drag data for other cylinder configurations in which the flow is not strictly two-dimensional, for example free-ended cylinders or cylinders joined to a plane wall, is less plentiful. Some results for the former case have been given by Wiesels-berger and others, obtained at Gottingen and NPL, have been presented by Goldstein.

This note discusses some preliminary drag measurements made for turbulent flow about circular cylinders which were joined to plane parallel walls at each end. Such configurations appear repeatedly in practice. The justification for applying the classical free-ended cylinder data to this problem is slight since, in this case, flow may occur round the ends of the cylinder from the high pressure region upstream to the low pressure wake.
The Subjective Basis for Aircraft Noise Limitation
Authors: Robinson D. W.
Published: July 2016

A brief review is given of the kinds of objective and subjective measurement required for systematic regulation of the aircraft noise around an airport, based on a maximum permissible noise exposure criterion. Some subjective factors are discussed and illustrated by test results.
A Look into the Future
Authors: Argyris J. H. , Patton P. C.
Published: July 2016

The up-to-date engineer or scientist would not challenge the growing importance of the modern large-scale digital computer in research and development. Yet, while we all agree that computers are important and useful, we disagree from one discipline to another and often within the same discipline on just what the computer contributes or can possibly contribute to research and development endeavours. The difference in approach to computer usage is more one of philosophy than of technique. Indications are given from our recent work that some philosophies of computer utilisation may be more fruitful than others. The availability of the large-scale digital computer has not only facilitated, but directly inspired and shaped the matrix methods for analysis of continuous media and structures, both in the linear and non-linear regimes. Without the availability of a modern computer all this work is literally meaningless.
Twenty-Second British Commonwealth Lecture
Authors: Dhawan S.
Published: July 2016

The Twenty-Second British Commonwealth Lecture, “Aeronautical Research in India”, was given by Dr. S. Dhawan, MA, BSc(Eng), MS, FRAeS, Director of the Indian Institute of Science, Bangalore, on 3rd November 1966. The Chair was taken by the President, Mr. A. D. Baxter, MEng, FRAeS, and the distinguished audience included His Excellency Dr. J. Mehta, High Commissioner for India.

Before the Lecture the President introduced Lord Caldecote, DSC, MA, FRAeS, immediate Past President of the Society of British Aerospace Companies Limited, who presented the four SB AC Scholarship Awards for 1966 to the recipients.

Introducing the Lecturer, Mr. Baxter said that the British Commonwealth Lecture had been established immediately after the Second World War to foster interest and understanding in aeronautical developments between Great Britain and her partners in the Commonwealth. He thought that object had been successfully achieved by the efforts of a long and distinguished list of lecturers, both from home and overseas; now they were to add another distinguished name to that list. Dr. Dhawan had taken his first degree in mathematics and physics at Lahore in 1938; in 1941 he obtained his MA from the Punjab University and, from the same university, his BSc in Engineering in 1944. After a period as an Assistant Supervisor with the Hindustan Aircraft Company, he was selected by the Government of India for advanced studies abroad in aeronautics. Dr. Dhawan had gone to the United States where he took a Masters Degree in Aeronautics at the University of Minnesota and a PhD in Aeronautics at the Californian Institute of Technology. Returning to India in 1951, he joined the Department of Aeronautics at the Indian Institute of Science, becoming Assistant Professor in 1952 and Professor and Head of the Department in 1955 and, since 1963 Director of the Institute.
Practical Applications of Planning Development Programmes and New Management Techniques
Authors: Dollimore G. P.
Published: July 2016

Present aerospace development work is done in an environment which demands success. This has stimulated interest in methods of planning and controlling project development and costs more positively.

While some developers continue to hold the view that planning other than in the broadest terms is not compatible with high novelty development, the importance of new planning attitudes has been recognised. However, the very magnitude of a major aerospace project is such that the application of new planning and control procedures may in itself constitute a significant development programme, and it is not surprising that the industry has shown caution in introducing major changes of method.
Axi-Symmetric Buckling of Orthotopic Circular Plates with Variable Thickness
Authors: Patel Sharad A. , Broth Franklin J.
Published: July 2016

Axi-symmetric buckling of a circular plate having different material properties in the radial and circumferential directions was analysed in ref. 1. A plate with constant thickness and subjected to a uniform edge compression was considered. The plate edge was assumed clamped or simply-supported. The analysis of ref. 1 is extended to include plates with thickness variation in the radial direction.
Cost Reduction and Cost Avoidance by Value Engineering
Authors: Ewans J. R.
Published: July 2016

I would like to thank the directors of British Aircraft Corporation (Operating) Ltd for permission to give this lecture, but I must emphasise that the opinions expressed are my own. I would also like to acknowledge the considerable contribution that has been made by every Value Engineer in BAC to the pioneering work of introducing Value Engineering into our Corporation, and thank all those, both in BAC and in other aerospace companies in this country and in the United States, with whom I have discussed Value Engineering, and whose ideas have contributed to this paper.
The Art of Aeronautics
Authors: Webb G. F.
Published: July 2016

As the Society's Centenary celebrations have shown, man first flew by sheer enthusiasm (and very little else). Many successful pioneers of aeronautics were untrained as engineers or scientists but—if art is the creation of form symbolic of feeling by “selection, not alteration”, then they were indeed artists.

By what means were their dynamic visions engendered?—how was their faith sustained? —and by what near-magical process of innovation was the utter beauty of man's flight attained? Although most of aviation is now engineering, the best of that remains an art. Where the engineer's factual experience nears its limits he relies for many of his ideas, attitudes and motivations on such everyday services as books, films, plays, newspapers and so on. The availability of relevant information at appropriate times has a critical bearing on the success of any project.

The efficient presentation of information is in itself an art, and the part played by those other artists who feed the aviation community with data—labouring to meet press dates, struggling on location, painting pictures or drawing cartoons—remains a vital force in the growth of aeronautics. Centenary Year would be incomplete without due acknowledgment of their efforts, and here are recorded a few examples of their achievements.
The Plate Buckling Coefficient
Authors: Bulson P. S.
Published: July 2016

The stability of a compressed plate is examined, using the energy method, with transverse deflections defined by a function giving the exact shape, but never specified. By this means it is possible to make observations about the form of the plate buckling coefficient. This form is examined tor two cases of loading, and it is demonstrated that a close approximation to the complete curve linking the buckling coefficient with plate aspect ratio can be deduced. The method is applicable to single plates or thin walled members consisting of an assembly of plates, and enables families of curves connecting buckling coefficients with aspect ratios to be summarised in a single relationship.
Boundary Shear Stress in Turbulent Boundary Layers on Smooth Boundaries
Authors: Rajaratnam Dr. N. , Froelich C. R.
Published: July 2016

It is well known that in the case of turbulent flow over smooth boundaries, the velocity distribution in the neigh- i bourhood of the wall is given by the law of the wall, c written as

whereuis the turbulent mean velocity at a normal distance of y from the boundary,u*is the shear velocity equal tobeing the boundary shear stress andρthe mass density of the fluid andvis the coefficient of kinematic viscosity. In the viscous sublayer, eqn. (1) becomes

and in the turbulent flow region above the sublayer and the transition region, foryu*/v> 30, eqn. (1) becomes

whereAandBare coefficients.
A Generalised System for Project Control and Evaluation
Authors: Mitchell George
Published: July 2016

An immediate requirement within the aerospace industry appears to be the development of a practical system for the evaluation and control of complex projects. No amount of qualitative evaluation will present management with the answer to the problem of making complex decisions. The Generalised System for Project Control and Evaluation presents an approach towards evaluation of quantitative indices of “value” and “cost effectiveness” that can be optimised, possibly by operational research methods, to produce information that can be used by management in the making of realistic decisions.
An Approach to Economic Space Transportation
Authors: Smith T. W.
Published: July 2016

This paper represents the personal views of the author and the objectives do not necessarily form any part of current official thinking.

Sooner or later, Europe is going to accept that it must indulge in space exploration and subsequent exploitation if it is not to lose its position as a principal technical community. While it may be conceivable that exploration may be undertaken by “small scale” activities, it is certain that exploitation will require a substantially greater capacity to deploy men and materials in space. This paper demonstrates the approach we would make to the problem of transportation of such payloads, which will be a basic part of such a venture, and the philosophy which leads to this approach.
A Calibration of a Turbine Flowmeter
Authors: Quarmby Alan
Published: July 2016

In recent years the use of turbine flowmeters in industry has become well established. An NEL publication by Myles and Harrison gives an excellent survey of their construction, use and calibration. It seems from ref. 1 that calibration by the manufacturers is done mainly with liquids, presumably in order to use a weighing technique to obtain the volume flow. A typical calibration report for a gas is that of Redding where the flowmeter in question was calibrated on air against a vena contracta tapped orifice. Eight experimental points are given on this calibration curve over the range of the meter. It was considered of interest to calibrate a turbine flowmeter on air against a pitot tube traverse. This method is generally regarded as being of greater accuracy than an orifice or nozzle method. Also it was considered that if a large number of readings were taken the amount of random scatter, if any, would become apparent.
World Survey, April 1965 Computer Utilisation for Structural Analysis
Authors: Robinson John
Published: July 2016

The utilisation of high speed digital computers for structural analysis is commonplace in the aircraft industry. However, despite this, no information appears to exist which indicates, nationally or internationally, the degree of utilisation in the various companies.

In an effort to give some indication a world survey was undertaken.
Non-Destructive Testing in Aircraft Servicing
Authors: Murden M.
Published: July 2016

During recent years, with the introduction of more complex aircraft structures, new techniques of aircraft servicing have been needed. It is essential to find even the smallest defects at a very early stage, but costly strip-examination must be avoided so far as possible.

Non-destructive testing is now playing an important part in this field, but many aeronautical engineers are unaware of the capabilities and limitations of the main methods.

This paper sets out to explain the basic principles of radiography, ultrasonic testing and eddy current testing. Since sampling inspections using these methods are now a mandatory requirement on all civil aircraft the paper should be of interest to all readers.
Proving the Design of Accessories
Authors: Lawrence J. O. N.
Published: July 2016

My Part of this discussion concerns development for reliability—the part after the original design and before production starts. But this stage cannot be divorced from the other two. All designs evolve from past experience of one sort or another or analogies. So new designs are evolved which use bricks or assemblies or mechanisms which have been used previously, even though perhaps in another way; these pieces have therefore been tested and there is practical experience of their behaviour. This applied to the original design. It is certain, however, that this will require modification, because in the confined space and with the extreme technical requirements demanded in the aircraft industry, any initial design will require modification—if not the scheme has been too pedestrian in concept and will be out-classed by competitive ideas evolved with more daring. Thus once again the designer needs development knowledge.
The Reliability of Military Aircraft—A User's Point of View
Authors: Mackenzie J.
Published: July 2016

I have been asked to express a user's viewpoint of what is required to ensure the adequate Reliability of military aircraft before their introduction into service, and to outline briefly what the Operational Requirements staff of the Royal Air Force are now doing to assist in this.

The problem of unreliability arises, particularly for military aircraft, from the increasingly complex systems which are needed to meet our stringent performance requirements. The reliability of equipment has not kept pace, and this has led to difficult and costly maintenance problems. These difficulties are further emphasised by tactical requirements which demand minimum maintenance in the field. The nature of STOL/VTOL operational aircraft and the need to deploy them with minimum support facilities is a special case where reliability is of outstanding importance.
Responsibilities of User Personnel
Authors: Coles R. B.
Published: July 2016

If You take a quick look at the subjects chosen for this Colloquium you will see that all except one have been, or will be, given by specialists and on their own subjects. In being invited to comment on the responsibilities of the user I have been presented with the unique task in this Colloquium of telling someone else what his job is. It is hoped, therefore, that the next ten minutes may provoke some lively discussion and will be taken in good part by anyone implicated.

Since the two speakers who follow are dealing with the way in which the user handles defects and defect records, it seems fitting to open with one or two comments on the user's responsibilities for this function, as seen by the manufacturer
Collection, Collation and Feed-Back of User Experience
Authors: de la Plain I. J.
Published: July 2016

About Half of the speakers so far have mentioned feed-back of user experience. Unquestionably, if we are to make real advances in reliability, Industry must be fed with comprehensive and timely data on the behaviour of its products in Service, and most of us would agree that the systems for data retrieval which exist today fall short of this requirement. It is inevitable, I suppose, that by the time we disperse from this meeting a number of problems within the whole field of reliability—whether to do with rig testing, responsibilities of sub-contractors, statistical prediction, contractual procedures, etc.—will have been thoroughly aired but not always with general agreement on them and in most cases without any feasible solution or break-through having been proposed. I suggest that the particular field of data feed-back is one where the requirement is almost unanimously agreed and where profitable and constructive steps forward are both identifiable and feasible.
A Resume of MoA Procedure
Authors: Butler A. R.
Published: July 2016

Group Captain de la Plain has said that certain defects are reported formally to MoA as the Supply Department. This paper outlines briefly some of the procedures involved in dealing with these reports, particularly those aimed at improving Reliability and mentions some forthcoming changes which have the same aim in view.

In the course of each year some 25 000 of these reports are handled by RDA (Defects) and in spite of “weapon concept” philosophies, some 200 different investigating authorities are involved. Since the capacity for investigation and re-design is limited, and because the traditional system for reporting does not discriminate sufficiently between important and less important defects, this mass of reports may prevent some defects from receiving the urgent attention they deserve. The Services have agreed therefore, to be more selective in their reporting since it is not possible to remedy every defect in existing aircraft and available effort must be directed into areas where the maximum improvement in aircraft safety, availability and reliability will result.
A Résumé of Methods of Contracting
Authors: Sarginson E. W.
Published: July 2016

Special reliability clauses have been introduced into a small minority of our contracts for military aircraft. This does not imply that reliability is otherwise ignored. Where operational requirements call for certain standards of reliability and where these are translated into equipment specifications or test schedules, the contract covers them in the same way as any other performance requirements. This has been particularly the case in contracts for aircraft engines.
Flying the X-15
Authors: White R. M.
Published: July 2016

I would like to begin by expressing my appreciation to the Society, especially the Test Pilots’ Group, and specifically to Bill Bedford for the invitation. It is a distinct pleasure and certainly an honour for me to be here. My discussion will centre on the X-15 research aeroplane, some of the essential items that we uncovered in our development flying programme and some characteristics of the aeroplane. I would hope I could go into this in sufficient detail. Being away from the programme for some time now, I have lost some of the intimacy that I had in the past but I think not completely so. At least, not enough so it will deny me the opportunity to present you with some information.
The One Hundred Days; 1965 Executive Actions; and the 1965—75 Timeframe
Authors: Worcester Richard
Published: July 2016

I took the unusual course of suggesting this lecture because I have something to say. I should have done this ten years ago. Better late than never. The position is that after £20 000 million spent on defence in the past 12 years, of which the air industry has had more than its full share, there is a culmination of industrial mismanagement, a crisis of confidence, a prevailing sense of bewilderment, an air of frustration and, therefore, a craving for new leadership in industry to make a true and worthy partnership of heart and mind with the active new leadership in Government. I sense moreover that behind the shadow boxing lies at this moment a more bi-partisan approach to meeting the future than immediately meets the eye. So this is not an exhortation but a demand to adopt new habits of thought that will lead to evolution of equipment calculated to sell well as a general rule instead of it being more the exception. And this is not a plea, but a demand, for a new resolve and leadership in industry coupled with a determination to make a better export showing in the 1970s on a smaller Government investment. The present Government's actions to promote research mergers and industrial co-operation with other countries seem a logical turning point for a re-start. So why not let us make resurgence date from now ?
Operational Research and Aviation Management
Authors: Jackson R. R. P. , Loncton P. A.
Published: July 2016

It is a sign of the present needs of the aviation industry that the Twentieth British Commonwealth Lecture, delivered by Mr. J. T. Dyment, Chief Engineer of Air Canada, was devoted to “Tools of Airline Management”.

In his lecture, Mr. Dyment pointed out that competition is too keen to permit Management to continue with methods satisfactory five or ten years ago and he reviewed some typical modern tools of Management. He mentioned a wide variety of tools both for the day-by-day control of airline activities, such as crew scheduling and for such strategic problems as the nurturing of the company image presented to the public. He paid especial attention to the way in which operational research in Air Canada has been able to assist Management in raising the efficiency of the airline.
Some Effects of Design Load Distribution on the Off-design Behaviour of Slender Wings
Authors: Squire L. C.
Published: July 2016

In order to trim a supersonic aircraft in the cruise condition it is often most efficient from the viewpoint of economic performance, for which a low drag is necessary, to use a cambered wing. The camber is designed to produce a chosen load distribution, but there is a wide range of suitable distributions. In view of this freedom of choice an investigation of the variation of Cm0 with design load has been made for a particular family of cambered delta wings. The calculations show that from the range of possible design load distributions it should be possible to choose one which results in Cm0 varying approximately in some desired way. Thus In principle It should be possible to choose a load distribution which satisfies the design requirements and results in improved off-design behaviour.
Bilateral Agreements
Authors: Jack Peter
Published: July 2016

In speaking to the Air Law Group of this Society, I speak as no lawyer and offer no legal profundities. I speak as an airline man, with some experience in bilaterals. I propose to talk upon some practical aspects of bilaterals as they appear to an airline man and to touch little upon “-isms” and “-ologies”. The philosophical profundities matter only if they help an airline to trade where it wishes and to plan ahead with some hope of continuity and flexibility of routeing.

I would like first to pay a tribute to the “only true begetter” of British policy in the bilateral field—Sir George Cribbett. It can have fallen to few Civil Servants to have had such influence on the commercial side of a great industry; it must be unique for such a man never even to have reached the principal post in his own Ministry. The very qualities which made his name so revered in the world at large were probably those which blocked his path at home. Our worldwide networks of today are his memorial. In the civil aviation field his epitaph might well be that on Wren's tomb in St. Paul's Cathedral—“Si monumentum requiris, circumspice”: if you seek his memorial, look around.
The Organisation and Control of Air Traffic in a Terminal Area
Authors: Jessell A. H. , Blake D. A.
Published: July 2016

There are several ways of judging the efficiency with which a terminal area is organised. Commercial operators are interested in the cost of the deviations or delays which they are subject to when using the principal terminal airports. Other users of the air space are concerned with the restrictions which terminal area procedures impose on their movements; while ATC (Air Traffic Control) authorities are interested in the cost of the ground facilities necessary to move the traffic with safety and expedition. In this paper we shall discuss mainly how delays and deviations may be minimised. Nevertheless, the procedures which result from this survey will lead to benefits for all and to a freer use of the terminal air space by other traffic.
The Impact of VTOL on the Air Transport System
Authors: Chichester-Miles I.
Published: July 2016

In comparison with the previous papers, this one is somewhat speculative in tone. In discussing commercial VTOL there is little hard fact to form a sound basis for extrapolation as there is with conventional aviation.

But we do know that relatively fast VTOL aircraft can now be engineered around the jet, the fan and the propeller. It also seems that VTOL may offer some peculiar advantages and bring about a significant increase in the capacity of the air transport system as a whole.

So it should be useful now to discuss in pretty broad terms the impact of the higher performance type of VTOL on the system: it will certainly be invaluable to the aircraft constructor to try to find out the influence of the whole air transport environment upon the design of the vehicle itself.
Ice From a Cloudless Sky
Authors: Carte A. E.
Published: July 2016

A large lump of ice fell from a cloudless sky one morning in September 1964 and landed only ten yards from a farmer in the Brits district of the Transvaal, South Africa. A whirring sound shortly before the impact alerted the farmer so that he saw the ice as it struck the ground.

The lump was flattish-shaped and irregular, estimated at 11 x 9 x 6 inches, and gave off a peculiar odour. The farmer also observed that the ice was composed of numerous layers and that parts of its interior were brownish-coloured. He did not recall noticing aircraft in the vicinity at the time of the incident.
Problems of Guided Weapons Development
Authors: Caldecote Lord
Published: July 2016

Development is the process by which a design conceived to meet a practical requirement is transformed from drawings, and perhaps a working prototype, to a piece of fully engineered hardware suitable for production which will meet the original requirement for performance (including reliability) and cost in a time-scale which makes it useful.

There are thus three main parameters in development: performance, cost and time, which are inextricably related to each other, and which must be constantly in mind during a development programme.

The technical aspect of development consists largely of optimising a basic design, making and proving individual parts of it, particularly where new technology is involved, and finally making and proving the complete equipment.
Airworthiness, The Board and Civil Aviation
Authors: Radlett H. C.
Published: July 2016

Events leading to the inception of the Air Registration Board are described, together with a survey of its make-up. The problem of airworthiness in general is dealt with in broad outline and a variety of problems which have been experienced are dealt with in more detail.
Results of a Research Programme to Develop the Aerodynamic Configuration of a Pitot-Static Tube Capable of Accurate Operation to Mach Number 5 and 150 000 feet
Authors: Smetana Frederick O.
Published: July 2016

A few years ago the United States Air Force became interested in developing a higher temperature version of its standard pitot-static tube capableA of accurate operation to Mach number 5 and 150 000 ft with angles of attack up to 14°. It soon became evident that the existing aerodynamic configuration was inadequate because (a) the sharp pitot pressure source could not be protected from high heat fluxes and temperatures, (b) the static pressure source geometry produced serious errors at Mach numbers above 3·0 for α> 5°, and (c) the static pressure source geometry could be responsible for unacceptably high lag above 100 000 ft altitude because it consists of two orifices of only 0·070 in diameter.
A Theoretical Analysis of the Influence of Rotation on Flow in a Tube Rotating about a Parallel Axis with Uniform Angular Velocity
Authors: Morris W. D.
Published: July 2016

When fluid flows in a tube which rotates about an arbitrary axis, the presence of centripetal and Coriolis acceleration components modify the velocity and pressure fields which exist in the absence of rotation. Barua considered the case of an incompressible fluid flowing in laminar motion through a cylindrical tube which was rotating about an axis perpendicular to itself with uniform angular velocity. For distances well away from the tube entrance Barua illustrated that secondary flow in the r-θ plane occurred and that the axial velocity profile was distorted towards the leading edge of the tube. Since the pressure gradient along the tube is proportional to the gradient of the axial velocity profile at the tube wall the rotation thus has a consequential influence on the resistance to flow offered by the tube.
Aviation in Perspective
Authors: Heinemann Edward H.
Published: July 2016

To have been chosen to deliver the 53rd Wilbur Wright Memorial Lecture is an honour of which I am very conscious and deeply appreciative.

Upon such an occasion I think it is appropriate that we pause to consider the truly great contributions made to aviation by Wilbur Wright, his brother Orville and the many pioneers who followed them, and to consider the effects of their contributions upon our lives.

I doubt very much if the Wright brothers in their most optimistic dreams could have imagined the tremendous progress aviation would make following their first powered flight 61 years ago.
The Bending of a Long Strip Reinforced by Transverse Ribs
Authors: Pope G. G.
Published: July 2016

When a long unreinforced flat elastic strip with free edges is bent to a uniform curvature about transverse axes in its own plane, anticlastic curvature is produced due to the influence of Poisson's ratio. Provided that the applied curvature is sufficiently small, the anticlastic curvature is constant across the strip and is proportional to the applied curvature. A finite deflection analysis shows, however, that the anticlastic deformation is reduced by the action of middle surface stresses, and the deformed strip approaches asymptotically a cylindrical form as the applied curvature is increased. Nevertheless, in some engineering applications it is necessary to limit the anticlastic deformation when the applied curvature is small, and for this purpose transverse ribs can be attached to the strip. In this note a small deflection analysis is given of the effect of uniformly spaced rigid ribs on the deformation of such a strip.
A New “Number” for Aircraft with Power-Augmented Circulation
Authors: Toms C. F.
Published: July 2016

The Familiar process of dimensional analysis for aerodynamics equates a force to a function of several variables liable to affect it, in terms of the dimensions M, L, T, and yields the numbers known as the Reynolds number and the Mach number of the flow. These numbers are generally regarded as useful and sufficient means of denoting the regimes of flow in conventional circumstances, where the force developed on a body results solely from the relative motion between the body and a mass of fluid.
Instrument Displays for Blind Flying
Authors: Green D. S. , Priestley E. , Holden K. J.
Published: July 2016

On behalf of my Company, which manufactures the RAE Head-up Display Equipment referred to in K. J. Holden's paper in the December 1964 issue of the Journal (pp 833-6), I would like to correct some misunderstandings which seem to exist and to amplify certain statements in this otherwise interesting and informative contribution to the techniques of instrument displays.

Dr. Holden states: “The essence of the (RAE) display is an attempt to reproduce the appearance of the runway as it would appear to the pilot.” This statement is incorrect as the flight director symbol to which he refers, is made up of a “target spot” (a’) and associated director lines (a) in Fig. 1. This symbol is a pure integrated flight director and is not and never has been intended to represent the runway.
Atmospheric Gusts
Authors: Zbrożek J. K.
Published: July 2016

Summary:—

Starting with atmospheric motions on a global scale, different categories of atmospheric turbulence are discussed. It is pointed out that the turbulence within the earth’s boundary layer is comparatively better understood than any other type of turbulence, due to a concerted effort by meteorologists and by aircraft engineers. Clear air turbulence, turbulence in clouds and storms are subjects of active research, but we are still at the beginning of the understanding of these phenomena.

The influence of atmospheric turbulence on some aspects of aircraft engineering is mentioned and the problem of the calculation or turbulence-induced loads is discussed in some detail. It is pointed out that the estimation of turbulence loads is a transposition of experience gained on one aircraft to another. The most simple technique of doing so is to assume that the atmospheric turbulence can be represented by a collection of single, isolated gusts and by making very simplifying assumptions about the dynamics of aircraft response. This technique, the discrete gust approach, in spite of serious theoretical reservations, has worked admirably well, but it appears that in many applications the limits of usefulness of the discrete gust approach have been reached. The alternative way of dealing with gusts is to treat them as a basically continuous phenomenon using the comparatively recently developed spectral technique. This technique not only permits the aircraft dynamics to be properly accounted for, but also describes the atmospheric turbulence in more realistic fashion, understandable not only to aircraft engineers but also to meteorologists and students of fluid dynamics.
Cowl Shapes of Minimum Drag in Supersonic Flow
Authors: Angus Boyd E.
Published: July 2016

Guderley, Armitage and Valentine have computed the inlet and closed body contours which form the forepart of an axially symmetric body, of given length and fineness ratio, having minimum pressure drag. The solution is not based on a simplified pressure law, such as the Newtonian impact law, because by a suitable choice of control surface for mass flow and momentum they are able to employ the general flow equations. It is clear, however, from an analysis of their tabulated results that their cowl shapes fall on a single curve for a given value of Δ=didt, the ratio of the initial to the final diameter of the cowl, when plotted in terms of a dimensionless length ξ=x/l and thickness η=y/dt, as in Fig. 1. Furthermore Fig. 1 shows that, except for small values of Δ, the Guderley shapes are indistinguishable from the optimum shapes calculated from Newtonian impact theory. The shape and characteristics of the Newtonian duct of given length and thickness, offering minimum drag to the external stream, are derived using the slender-body approximation. Ducts for which Δ > 0.04 are shown to be sufficiently slender. The slopes of those with 0 ≤ Δ < 0.04 are too large only in a small critical region near the nose. Thus slender body theory will give a close approximation to the exact Newtonian solution even in these cases. For the larger values of Δ likely to be used in practice slender body theory is valid everywhere.
Future Relationships between Air and Ground Transport
Authors: Brancker J. W. S.
Published: July 2016

Perhaps the most encouraging thing about the article by Mr. J. R. Cooper entitled “Future relationships between Air and Ground transport” which appeared in your issue for November, is that someone at least is ready to consider unorthodox methods of solving some of our present problems. It is a difficult paper on which to comment effectively because its does, as the author admits, embrace three separate principles.
The Initial Buckling of Slightly Curved Panels Under Combined Longitudinal and Circumferential Direct Stresses
Authors: Sayers K. H.
Published: July 2016

The initial buckling stresses of rectangular panels under applied axial loads are in general increased both by circumferential tensile stresses and by the curvature of the panel. The present Note gives theory to estimate these stresses for panels forming part of an unstiffened cylindrical shell. All edges are free to rotate. This condition is often closer to the actual rotational edge restraint of curved panels in conventional stressed-skin construction than the clamped condition, especially in the case of lightly-reinforced shells. The axial generators in the mid-plane of the panels are held straight at the longitudinal edges. All other axial generators are also assumed to remain straight before buckling (no “mattress effect”). The middle surface is restrained at the curved edges of the panel against radial deformation during and after buckling.

Design curves are presented for several values of the parameter (ab/Rt), followed by a typical example.
On the Determination of the Natural Frequency of a Star-Shaped Membrane
Authors: Laura Patricio A.
Published: July 2016

The natural frequency of the fundamental mode of star-shaped membranes whose boundary is given by an equation in polar form is determined. The boundary conditions are satisfied identically by conformally transforming the complicated shape onto a unit circle. The transformed partial differential equation is solved by two different collocation techniques.
Investigation of the Physical Properties of Gases at High Temperatures
Authors: Lapworth K. C.
Published: July 2016

At the very high flight speeds of ballistic missiles, re-entering satellites and meteorites, the air in contact with the body may attain very high temperatures and may even become ionised. For example, the air in the stagnation region of a low-drag ballistic missile re-entering the Earth's atmosphere can reach a temperature of 8000°K and the electron density may be as high as 1016 per c.c. In any experimental work on high enthalpy flow it therefore becomes necessary to have techniques for measuring these high temperatures and high electron densities. The aim of the present paper is to describe techniques for measuring these quantities.