bluuebunny/crossref_metadata_2025 huggingface dataset:
An Integral Relationship for Boundary Layer Flow
Authors: Whitehead L G.
Published: November 2014

AN approximate solution of the boundary layer equations recently completed involved the assumption of a velocity profile through the boundary layerdepending on two parameters. As a result the problem was reduced to that of the construction and solution of two equations governing the variation of these parameters around the surface of the cylinder considered. Earlier solutions, such as Pohlhauscn's, have made use of a single parameter only and have employed Kármán's momentum integral for its determination, but the additional, parameter now introduced necessitates the use of a further equation. It is the purpose of the present note to discuss and illustrate the properties of the second condition that was selected.
Boundary Layer Calculations
Authors: Piercy N.A.V. , Whitehead L.G.
Published: November 2014

ANOTHER paper (Ref. 1) establishes a new approximate solution of the boundary layer equations devised to meet difficulties that are encountered in applying earlier solutions to laminar flow aerofoils and similarly thin cylinders. The advantage is in respect sometimes of accuracy, sometimes of applicability. The solution is a little unwieldy in its general form, however, and the present paper describes simplifications to facilitate rapid technical use. They are of two kinds, one being much more drastic than the other, and that first given, or both, may be used according to the nature of the problem and the accuracy required. Examples suggest that the resulting loss of accuracy and applicability will be small in most instances. This matter is described in Section I.
A Note on Natural Frequencies
Authors: Krzywoblocki M.Z.
Published: November 2014

THE aim of this paper is to calculate the natural frequencies and to consider the influence of the damping parameter on a wing's natural flexural and torsional vibration. The author took into account only the elastic hysteresis of the material because the structural damping, depending on the type of the aeroplane, cannot be taken into account in a general consideration.
Rivet Flexibility and Load Diffusion
Authors: Mansfield E.H.
Published: November 2014

THE problem of load diffusion from a boom into a stiffened sheet structure has been considered by many writers. The solutions obtained lead to an infinite shear stress at a point at the free edge of the sheet adjacent to the boom. They are therefore of little practical value in determining the necessary strength of the boom‐to‐sheet connexion.
Mechanical Tests and the Working Properties of Metals
Authors: Fitzgerald‐Lee G.
Published: November 2014

FOR buyer and manufacturer alike today materials must satisfy recognized standards in their physical and mechanical properties. Thus, tests yielding comparative data are essential in determining the right material for any particular purpose.
The Elementary Theory of Stressed‐Skin Construction
Authors: Hemp W.S.
Published: November 2014

CONSIDER a fuselage or wing structure in the form of a reinforced cylindrical tube. We shall base our analysis of the equilibrium conditions of this structure upon the assumptions outlined in 2.6. In particular referring in the first place to a skin panel lying between adjacent stringers and rings, we remark that this panel carries only shear stresses and is free from external forces. It follows, as we have observed before, that this panel must therefore be in a state of uniform shearing and so must apply uniform shear flows at its lines of juncture with the adjacent panels and the reinforcing stringers and rings. The equilibrium conditions to be satisfied at a stringer‐skin joint are now clear. The panels adjacent to the stringer apply different, but uniform, shear flows, to the line of attachment. The reaction from the stringer is determined by the rate of variation of its end load, for this clearly gives the rate of load input into the stringer. Adopting a consistent sign convention for the shear flows in the several skin panels we can thus enunciate the following theorem:
The Determination of Redundant Constraints in Beams
Authors: Manton F.E.S.
Published: November 2014

IN what follows n‐2 equations have been obtained, valid for all kind of beams having n rigid level supports, and which are either:
Some Structural Parameters for an Aero‐Isoclinic Wing
Authors: Mansfield E.H.
Published: November 2014

The general theory of the clastic behaviour of a conventional single‐cell wing stiffened with swept ribs (or stringers) has been dcvclopcd. It was shown that the swept members introduce a measure of skewness in the structural geometry of the wing which cause the wing to twist, as well as bend, under simple bending loads. This note shows that, if the sweepback angle is not more than 35 deg., it is possible to make a wing aero‐isoclinic by introducing swept stringers.
The Alleviation of Thermal Stresses
Authors: Parkes E.W.
Published: November 2014

The following paper investigates the dependence of the thermal stresses which are set up when an aircraft suffers an external temperature change, upon the degree of insulation of the outer skin, and upon the speed with which the external temperature change takes place. It is shown that quite thin insulating layers, such as are provided by the aircraft paintwork, can produce considerable alleviation of the thermal stresses. We should not generally, however, expect any appreciable reduction in the stresses due to the finite time taken for the external temperature to change, since effectively instantaneous variations of temperature can occur in practice, particularly when the external surface is insulated.
The Library Shelf
Authors: P.L.T.  , A.S.F.  , A.G.P.  , H.B.H.
Published: November 2014

For 5,000 years man has had experience of metal. Considerable though this period is, if judged on an historical rather than on a geological basis, it has proved all too short for the determination of the major chemical and physical characteristics of even that small group of metals used in engineering. This lack of knowledge is particularly conspicuous with regard to the property, now called ‘Fatigue’, whose very existence was not recognized in this country until 1849.
Theoretical Aspects of Flame Stabilization
Authors: Spalding D.B.
Published: November 2014

An approximate graphical method of calculation is presented for evaluation of the flame speed of premixed combustible gases and its relation to the minimum size of burned gas pocket which can propagate a flame. The theory is applied in a semi‐quantitative manner to the problem of the stability limits of a flame anchored to a bluff body in a stream of high velocity gas. Three different approaches to this problem are made, each of which indicates that the velocity of the gas stream at blow‐out should be proportional to the linear dimension of the flame‐holder, the absolute gas pressure, and the square of the laminar flame speed of the combustible gas.
Structural Aspects of Swept‐Back Wings
Authors: Noton B.R.
Published: November 2014

THE efficient design and construction of the latest types of Swedish military aircraft, with wings with high critical Mach numbers, has necessitated a thorough investigation into the structural behaviour of swept and delta wings of both the thin and thick types. It is the main purpose of this paper to present some important test results and pertinent details of some of the small scale models which have been built to supplement the theoretical estimation of the stress distribution and deflexion patterns. In some cases these models have also been constructed to provide information on certain unusual structural configurations, which would have otherwise taken many months to obtain by using approximate theoretical methods. The stress distributions for each model are illustrated in such a way that comparison between the different types of structures may readily be made.
The Normal Modes of Vibration of an Aircraft
Authors: Shevloff N.P. , Reid T.J.
Published: November 2014

In order to provide information for flutter and dynamic stress calculations on an aircraft a knowledge of the normal modes of vibration is required. In the following paper a matrix method, due to Dr Traill‐Nash, is extended and used to obtain a general expression for the complete aircraft normal modes, and is applicable to most aircraft configurations. The method is considered to be eminently suitable for use with modern digital electronic computational equipment. Methods arc discussed vthcrcby the degrees of freedom may be economized without significant loss of accuracy. By restriction of the degrees of freedom allowed, important subsidiary cases arc drawn from the general expressions, allowing standard matrix solutions suitable for normal oflicc routine.
Transient Thermal Stresses in Wings
Authors: Parkes E.W.
Published: November 2014

The following paper discusses the transient thermal stresses set up in a cellular wing structure when the aircraft is subjected to a change of speed or of altitude. It is found rftac for nings with little or no insulation (fie maximum stress in the wing is usually between 70 per cent and 85 per cent of the value given by Young's modulus for webs × coefficient of expansion for the skin × external temperature change: it is therefore concluded that of the metallic materials, the combination of Hfcht alloy webs with a steel skin is admirable in its effect in reducing the thermal stresses. The analysis used is exact within the limits of its assumptions and comparisons are made with an earlier solution of the same problem by Hoff, who used an approximate method.
Stability and Strength of an Undercarriage Radius Rod
Authors: Person P.
Published: November 2014

An undercarriage radius rod arrangement frequently employed comprises articulated members having a retraction jack locked internally in the down position to stabilize the system. The loads from the ground cases induced in the members are dependent upon the geometry of the system and also the clastic properties of the members and their respective airframe pick‐up structure. The conditions for structural stability are analysed and a method is given for determining the nominal offset of the radius rod knuckle to achieve an efficient strength‐to‐weight ratio for the structure.
Energy Theorems and Structural Analysis
Authors: Argyris J.H.
Published: November 2014

IT is natural in reviewing the developments of Sections 3 and 4 to inquire if it is possible to enlarge upon the conception of complementary work and strain energy in a similar way as accomplished for work and strain energy by the introduction of virtual displacements.
Maximum Lift Data for Symmetrical Wings
Authors: Nonweiler T.
Published: November 2014

We shall attempt here to summarize the existing data on the values of the low‐speed CLmax. of wings, in the absence of a fuselage, and without including information on stalling incidence or pitching moment. The summary is limited to the consideration of unswept wings, and those of delta plan form, which have symmetrical sections: there is some discussion of the maximum lift increments due to the use of flaps of various kinds.
The Library Shelf
Authors: D.W.H.  , C.H.S.  , J.T.
Published: November 2014

The first edition of this book was published in 1947, and dealt almost exclusively with the design and operation of low‐speed wind tunnels. In the present edition much of the original material has been revised and brought up to date, and additional chapters have been added to extend the description to wind‐tunnel testing at high subsonic, transonic, supersonic, and hypersonic speeds. The growing importance of rotary‐winged aircraft has led to the inclusion also of a short chapter on the testing of helicopter rotors.
Energy Theorems and Structural Analysis
Authors: Argyris J.H.
Published: November 2014

THE general theorems given in Sections 4 and 6 include, from the fundamental point of view, all that is required for the analysis of redundant structures. However, to facilitate practical calculations it is helpful to develop more explicit methods and formulae. To find these is the purpose of this Section.
The Library Shelf
Authors: R.N.L.  , B.R.N.  , E.G.B.
Published: November 2014

This book is an extension of a series of lectures given at the Institute of Aeronautics of the University of Brussels. It gives the aerodynamic theory of the helicopter rotor in complete detail, and with some 130 sketches, diagrams, graphs and photographs, and the reader need not have any previous knowledge of the subject.
Fatigue Tests and Aircraft Life Evaluation
Authors: Haas Tibor
Published: November 2014

THE method used at present in fatigue testing aircraft joints and components by applying cycles of constant stress amplitude of a magnitude considered to be the most damaging is based on the assumption that Miner's cumulative damage rule, Σ(n/N)&equals l, holds good. This rule is known to be true only under certain conditions which may not apply to those under which fatigue damage is accumulated in aircraft.
Nozzle Flow with Heat Transfer and Friction
Authors: Gordon Watson W.
Published: November 2014

THE problem of the expansion of a compressible fluid with friction and heat flow is one of great complexity. In this treatment it has been simplified to a one‐dimensional problem and the resulting relationships are thermodynamic. An expansion of this type cannot be described as reversible due to the presence of friction, and from this aspect the analysis may be suspect. However, any practical process is irreversible and it is common practice to apply to such processes an analysis which is theoretically confined to changes which occur reversibly. Thus, although the degree of irreversibility may be greater than usual in this case, there are many precedents for allowing the use of reversible thermodynamics in the analysis of irreversible changes. The relations for the expansion are well known, but the writer believes the analysis and discussion on the choking conditions of a nozzle are more general than anything yet published.
International Colloquium on Fatigue of Metals
Authors: Noton B.R.
Published: November 2014

FATIGUE of aircraft structures has recently become an important subject, particularly during the last two years, and many research organizations and aircraft manufacturers are now engaged in investigations into the problems of fatigue. Three international events dealing comprehensively with most aspects of fatigue have been arranged, and the first of these, organized by a Swedish committee of the International Union of Theoretical and Applied Mechanics, took place last May at the Kungliga Tekniska Hogskolan in Stockholm. The second conference, specifically concerned with fatigue of aircraft structures, will be held from January 30 to February 1, 1956, at Columbia University, New York. (Information may be obtained from Professor A. M. Freudenthal, 716 Engineering, Columbia University, New York 27, N.Y.) The entire field of metal fatigue will be covered by the third conference, organized by the Institute of Mechanical Engineers, to take place in London from September 10 to 14, 1956.
On the Buckling of Oblique Plates in Shear
Authors: Wittrick W.H.
Published: November 2014

If a thin oblique plate (i.e. in the shape of a parallelogram) is subjected to a uniform shear stress parallel and perpendicular to two of the sides, the critical value of the stress depends on the direction in which it is applied. The higher critical value is obtained when the shear is tending to decrease the obliquity of the plate. The ratio between the two critical shear stresses lies between 1 and 8 for a simply supported 45 deg. oblique plate and between 1 and 2·69 for a clamped 45 deg. oblique plate. This paper discusses the phenomenon for 45 deg. oblique plates and shows that even for plates of practical proportions the ratio between the two critical shear stresses may be of the order of 4 if the edges are simply supported.
The Library Shelf
Authors: J.M.  , Mc C. A. , J.E.D.
Published: November 2014

The cardinal purpose of mathematical analysis is to establish the validity of the concepts, theorems and artifices which comprise the mathematical machine, and to prescribe the limitations and reservations to which the operations by this machine are subject.
The Specification and Testing of Fine Particle Filters
Authors: Cranston R.W. , Beynon L.R.
Published: November 2014

A method of defining the filtration efficiency of filter media has been devised, in which the transmission factor at a specified size is measured instead of the effective cut‐off size. The new measure is more sensitive and provides a more useful fiure than the old measure of effective cut‐off size. An additional test is proposed to measure the efficiency of removal of particles of smaller sizes; this test requires the derivation of the transmission curve, which is defined. No change is proposed in the method of measurement of flow efficiency in terms of flow constant. It is suggested that the specification of a fine particle filter medium should include the following clauses: (a) A statement of the maximum acceptable transmission factor at a given size (cither 5 microns or 10 microns). (b) A statement of the maximum acceptable transmission factors at various smaller sizes. (c) A statement of the minimum acceptable flow constant. Experimental techniques, including the method of preparing the artificial contaminants, are described. Results are presented on nine materials and a comparison is made for five of these materials between transmission factors at 5 microns and 10 microns and effective cut‐off sizes. The dependence of transmission factor and flow constant on thickness of filter medium is discussed.
Some Aspects of Turbojet Performance Calculation at High Flight Mach Numbers
Authors: Palmer J.R.
Published: November 2014

AT the present time turbojet aircraft types which are capable of level flight Mach numbers well into the supersonic range are appearing in increasing numbers. Yet, while this represents in a sense a new phase in the evolution of piloted aircraft, from the point of view of the propulsion engineer it is rather the end of an era, in that hitherto the turbojet engines employed have been essentially subsonic engines suitably strengthened. Henceforth we may expect to see the use of engines specifically designed for the appropriate range of Mach number, and it is the purpose of this article to review some of the implications of this change of outlook in so far as they affect the prediction of engine performance.
Incremental Collapse Due to Thermal Stress
Authors: Parkes E.W.
Published: November 2014

WHEN a structure is subjected to a recurrent cycle of loading a number of different types of deformation may be set up. The structure may remain elastic throughout, returning to its original configuration at the end of each cycle. It may shake down to an elastic configuration which differs from the initial one, but which, once established, is the same at the end of each cycle. The structure may suffer inelastic deformation in each cycle of loading, with net value zero, so that again the configuration is the same at the end of each cycle: this condition is usually known as alternate plasticity and may lead to strain fatigue. Finally, the structure may suffer inelastic deformation in each cycle which has a non‐zero net value, so that the deformation changes progressively with each cycle of loading: this is known as incremental collapse.
Matrix Analysis of the Circular Conical Fuselage
Authors: Goodey W.J.
Published: November 2014

METHOD for the stress analysis of the circular conical fuselage with flexible frames, subjected to a fairly general type of load distribution, was recently developed by the present writer in a paper published in the Journal of the Royal Aeronautical Society. This paper did not, however, make any attempt to deal with the question of cut‐outs, and for the reason given below it later transpired that certain modifications of the basic theory were required before this problem could be solved.
Matrix Analysis of the Circular Conical Fuselage
Authors: Goodey W.J.
Published: November 2014

THE strain energy (UF) in a frame is expressed by the equation
The Stresses in a Plate due to a Local Hot Spot
Authors: Parkes E.W.
Published: November 2014

An analysis is given for the stresses in an insulated plate in the neighbourhood of a local hot spot. The stresses depend upon the relative size and flexibilities of plate and heated area.
Matrix Analysis of the Circular Conical Fuselage
Authors: Goodey W.J.
Published: November 2014

IN this part we shall consider the effect of non‐uniformity (with respect to k) in the longitudinal members, with particular reference to the case of four longerons, and we shall then go on to discuss the treatment of cut‐outs.
Ground Loads on Aircraft Undercarriages at Touch‐down
Authors: Blinkhorn J.W.
Published: November 2014

THE most severe ground loads to which an aircraft undercarriage is subjected when landing usually occur during the fraction of a second following the instant of touch‐down. Generally, less critical ground loads occur during the landing run, e.g. due to the application of wheel brakes, turning or swinging of the aircraft, the wheels striking obstacles, unevenness of runway, etc.
Simple Shielded Total‐Pressure Probes
Authors: Winternitz F.A.L.
Published: November 2014

Design features and characteristics of conventional, modified and shielded total‐pressure probes are briefly discussed, and compared with new shielded instruments of simple construction which combine smallness of size with adequately fast response to pressure changes. Tests at air speeds up to 280 ft./sec. showed that a probe featuring a total‐traversing cylinder with single orifice inside a tubular shield will register total pressure to within 1 per cent of the dynamic pressure up to inclinations of the flow of ±28 deg., the error in the range ±22 deg. being less than 0.5 per cent. The response time of the instrument under a suddenly applied air pressure of 500 mm. W.G. was less than 60 seconds when linked to a Betz projection manometer. If the inner cylinder is replaced by a central sting, the range of insensitivity to flow inclinations is increased to ±45 deg., the error being less than 0·5 per cent of the dynamic pressure. The response time of this probe under 500 mm. W.G. air pressure was approximately 100 seconds. Still simpler versions of the instruments described are under development.
Helicopter Ground Resonance
Authors: Hooper W.E.
Published: November 2014

The equations of motion developed by R. P. Coleman have been evaluated for a particular helicopter configuration and a large number of different combinations of rotor and fuselage damping. These results are displayed graphically and reveal the dependence of the unstable range on rotor and fuselage damping. Some of the conclusions are in disagreement with those reached by Coleman. Both viscous and friction rotor dampers are considered.
The Library Shelf
Authors: E.L.J.  , D.B.S.  , A.D.B.
Published: November 2014

The author in his preface states that the text should serve as a stepping stone between introductory dynamics and the more advanced fields of engineering analysis and that the development of the theory as a carefully planned sequence of concepts has made possible the inclusion of much material (for example, such topics as transient phenomena, self‐excited vibration, and control systems) not ordinarily dealt with in an introductory course.
Titanium and Aircraft Engineering
Authors: Kennedy A.J. , Sollars A.R.
Published: November 2014

TITANIUM, with a melting point of 1,660 deg. C, higher than that of nickel or iron, a density little more than one‐half that of steel, and a corrosion resistance in certain environments superior to stainless steel, is evidently a metal of significance to aeronautics. In the last few years remarkable advances have been made in both the production technology and the basic physical metallurgy of the titanium alloys, and it would be fair to say that aeronautics generally has not exploited the possibilities of these alloys to the extent that might have been expected. This is in part due to economic factors, as titanium is still relatively expensive, and in part due to a lack of conviction in the relative advantages which the alloys can offer. It is obvious that as more titanium is brought into use in aeronautics, so the economic aspect will improve, and the more experience will designers and materials engineers generally gain in its utilization. The purpose of the present article is to survey some of the basic metallurgical considerations which enter into the development of the titanium alloys, and relate these to the specific engineering factors of interest in aeronautics. This will lead to a discussion of the ways in which the titanium alloys are being introduced into aircraft structures and engines. The subject is clearly a very large one to attempt in a single article, and many quite important topics have necessarily been abridged or omitted altogether. The references should, however, make it possible to follow up individual subjects in more detail.
The Library Shelf
Authors: J.C.
Published: November 2014

Stranded on a desert island or in a hospital bed with only one book to read, the victim can do far worse than have a good dictionary on his favourite subject. You flick over the pages to look up something you want to know, your eye catches an adjacent entry which intrigues you and you are off on the fascinating game of being referred from one entry to another in your pursuit of knowledge. If the game is not to lead to frustration and anger the book must play fair by you, it must leave you with the feeling that you have really learnt something for your efforts, even if occasionally this is that the subject is too abstruse for concise treatment and you are fobbed off with a list of references.
The Library Shelf
Authors: A.D.Y.
Published: November 2014

One of the most significant features of post‐war engineering has undoubtedly been the rapid growth of automatic control techniques and their widespread application. The importance of this development can be gauged not only by its technical possibilities but also by the fact that it is associated with its own theoretical tools and language with which to re‐examine old problems as well as to study new ones. Closed and open loop systems, feedback, transfer functions, and the use of operational calculus are rapidly becoming familiar elements in the speech and theoretical usage of engineers; and they are being accompanied by important changes in engineering philosophy. The functions of automatic control theory, or cybernetics, as it is sometimes called, were laid by Norbert‐Wiener and his colleagues, who were also responsible for the development of the related subject of Information Theory. An important problem of the latter topic is that of the response of an oscillatory system to a random input disturbance or noise. The successful solution of this problem has again had widespread applications, since essentially the same problem arises in many branches of engineering.
The Estimation of Tail Loading Due to Elevator‐Induced Pitching Manoeuvres
Authors: Richards P.F.
Published: November 2014

By application of the analytical method to a wide range of current aircraft types an approximate form of the method is developed for the quick estimation of tail load maxima and associated torques during the checked manoeuvre and the same is also confirmed for the unchecked manoeuvre of Ref. (3). Numerical values of critical elevator actions to be associated with the airworthiness design case are considered and hence, from a comparison with the approximate method, the limitations of the present empirical approach given in British and American civil airworthiness regulations are brought to light.
The Library Shelf
Authors: D.B.S.
Published: November 2014

The current issue of Combustion and Flame contains five papers which will interest aircraft propulsion specialists. They have in common that they are all American and that they are all rather difficult to digest. Two are concerned with air‐breathing combustion, two with solid propellent rockets, and one with liquid propellent rocket motors.
The Library Shelf
Authors: D.J.M.
Published: November 2014

It is about fifteen years since the word hypersonic was used to distinguish the characteristics of the flow of a gas at high Mach numbers, say greater than five, from those of a gas at low, supersonic Mach numbers.
Auxiliary Systems
Authors: Trotman C.K.
Published: November 2014

AT the end of the war in 1945, aircraft systems could still be classified as ‘auxiliary’ and ‘ancillary’—those which were essential for flight and those which were installed for reasons of safety, crew or passenger comfort and operational efficiency. Thus auxiliary systems generally included only the fuel system and ignition system, and many aircraft, particularly military, were flown into repair depots with one or more of the ancillary systems inoperative.
Design of a Pressurized Missile Body
Authors: Houghton D.S. , Chan A.S.L.
Published: November 2014

THE structural design of a long range ballistic missile or a space rocket vehicle is an intriguing problem. It is hardly necessary to stress the importance of achieving as light a structure as possible, since any unnecessary increase of structural weight can severely affect its performance or result in a profound increase of its total weight. There is a dearth of published information on this subject, presumably because of security restrictions. Among the papers available, only Sechler dwells on the structural design consideration in any detail. We have therefore very few specific facts to guide us, and can only relate the problem to our aircraft design experience with commonsense.
Second International Congress of the Aeronautical Sciences
Authors: Johns D.J.
Published: November 2014

A report is given on the above Congress which was attended by approximately 550 delegates from twenty‐seven countries. The sixty papers presented embraced the subjects of aerodynamics, materials, structures, propulsion, air transport, aerospace medicine, space Hight and re‐entry; a selection of these papers are summarized below.
Synthetic Lubricants for Gas Turbines
Authors: Elliott J.S. , Edwards E.D.
Published: November 2014

SINCE the Second World War, no lubrication problem has offered a greater challenge to chemists than that posed by the aircraft gas turbine engine. Mineral oils, which for many years had provided satisfactory lubrication of piston‐engined aircraft, had obvious limitations when considering jet engines, and more than ten years ago the need for new lubricants was realized. The requirements were improved high temperature performance coupled with low volatility, fluidity at low temperatures, and high load‐carrying capacity. The requirements of satisfactory lubricants for aircraft gas turbine engines were discussed as long ago as 1947 by Williams, who proposed certain tentative test methods and pointed out the limitations of the mineral oils currently in use. At that time research on potential synthetic lubricants had begun both in the U.K. and in the U.S.A., and during the next four or five years bench engine tests were carried out, followed by flight trials in aircraft.
Queen Mary College, University of London
Authors: Young A.D.
Published: November 2014

AERONAUTICS owes much to the selfless devotion and enthusiasm of its early pioneers. As was noted by the author in the Fourth Lanchester Memorial Lecture,1 Queen Mary College can claim to have the oldest established University Department of Aeronautical Engineering in the country due to the pioneer work of Dr A. P. Thurston, a graduate of the College, t It was in 1908 that he decided to establish an Aeronautical Laboratory there. He inspired the interest and support of like‐minded friends and Mr P. Y. Alexander, in particular, contributed a major part of the funds required to equip the laboratory. From Professor J. L. S. Hatton, the then Principal of the College, Dr Thurston received warm encouragement and the space for the venture, but College funds were then less than adequate for its longer established activities, and so the College could not afford to offer financial support to the new venture in its early days.
Engine Design Trends—II
Authors: Hooker S.G.
Published: November 2014

THE paper by Mr Morley has illustrated in excellent fashion how the continued requirements for better fuel consumption, more thrust or power per unit of engine weight, more thrust or power per unit of frontal area, has caused the relatively simple Whittle jet propulsion engine to develop into the highly complex aircraft gas turbine of today. Of all the means of transporting people and goods about the surface of the earth, the aeroplane responds more rapidly to technical advances in the method of propulsion than any other piece of equipment (excepting, perhaps, rockets), and this applies not only to speed, range and altitude of operation, but also to the most important problem of operating costs. As a consequence of this, we engine designers are constantly being faced with the necessity of creating new ‘technical triumphs’ in any new engine that we design, and this is the driving force which causes us to complicate the design and, hence, the manufacture of many of the components.
Aeronautical Development in Brazil
Authors: Legg K.L.C.
Published: November 2014

The author has recently returned from Brazil after completing a four‐year contract with the Brazilian Air Ministry. This paper presents some views and developments resulting from this experience and relates them to the potential and important field of co‐operative aeronautical development programmes between Britain and countries with a rapid rate of industrial detelopment such as Brazil. The paper commences with a general review of current aeronautical development in Brazil and then presents a relatively detailed account of initial project work relating to an executive/transport aircraft. Throughout these phases accent is placed on the difference of outlook of a people who are looking towards a great future development of their country. It is finally concluded that there is a potentially large development market in which Britain can and should take a leading part and from which could eminate substantial mutual advantages. This co‐operation should however only be undertaken on a national basis and with a full understanding of the particular conditions relating to such countries.
Assessing Helicopter Safety with Respect to Component Fatigue
Authors: Hall A.D.
Published: November 2014

A distinction is drawn between reliability, and aircraft safety, which may be termed a subdivision of reliability. Some principles arc laid down that will enable the aircraft development programme to proceed upon the necessary lines to meet requirements for safety. The procedure uses statistical methods of data analysis because at the present state of knowledge these provide the sole means for the mathematical determination of reliability from the safety aspect. As safety requirements have not yet been specifically stated, a suggestion has been made that aircraft safety should require a catastrophic failure rate of less than 10–3after 10,000 flying hours. It has been shown how a requirement of this type may be met, but the methods are sufficiently flexible for adaptation to any requirement that may be considered necessary in the future.
Rotor Dynamics ROTORCRAFT and Helicopter Stability
Authors: Price H.L.
Published: November 2014

The ultimate object of the present work is the investigation of the dynamic stability of a helicopter. Fundamentally this is the problem of the small oscillations of a body about a steady state of motion when subjected to a field of force comprising aerodynamic and gravitational forces. It may be remarked in passing that there is really no such thing as a steady motion of a helicopter. The rotor forces are continually varying during the course of a revolution, and the notion of a steady motion has to be interpreted as ‘steady on the average’. With this proviso the problem is intrinsically the same as that of the stability of a fixed wing machine, and the problem reduces to finding the variation of the rotor forces when subjected to small disturbances and feeding this information back into the equations of disturbed motion of the helicopter as a whole. Naturally a proper estimation of the forces in the disturbed state depends on a faithful description of the initial steady state, and for this reason the previous account of the steady motion is included. In particular, the increments in the rotor forces due to a disturbance will be functions not only of U, V, W but also of ?0, ?1, ?2 and ?0, ?1, ?2. The flapping angles themselves, however, will vary during the disturbance, and much of the work will be concerned with calculating the effect of this variation on the rotor forces as a whole. In general ? and ? will be fairly small; but, whereas in stability theory the products of small velocity increments are ignored, products here of ? and ? will warrant a great deal of attention. The retaining of second order terms throughout would be a formidable task, but as mentioned earlier, it is possible to enunciate a general principle enabling only the more important products to be selected.
Recent Changes in Aviation Journalism
Authors: Oliver Stewart Major
Published: November 2014

This article is based upon a paper presented by Major Oliver Stewart to a meeting of The Historical Group of the Royal Aeronautical Society on March 19, 1962, just a few days after the last issue of Major Stewart's own monthly aeronautical journal ‘Aeronautics’ was published. Although some fifteen months have now elapsed since the original paper was presented, it has continuing relevance at this time as the British aeronautical press undergoes further changes. To mention but three examples, the journal ‘Airport and Airline Management’ ceased publication with its May I June 1962 issue, the English language edition of the French ‘Aviation and Space Magazine’ ceased publication with its April 1963 issue, and ‘Aircraft Production’ became a general production engineering journal as from the April 1963 issue. There can be few people better qualified to describe the changing scene of aeronautical journalism, for apart from his experience as a ferry pilot and single‐seat fighter pilot during the First World War and subsequently as an experimental and test pilot at Orfordness and Marilesham Heath, Major Stewart has been aeronautical correspondent of ‘The Morning Post’ (1926–37), ‘The Times’ (1939), ‘The Evening Standard’ (1940) and ‘The Manchester Guardian’ (1941–58). In addition, he was, of course, Editor of ‘Aeronautics’ from the time of its birth in 1939 until its demise last year.
Take‐Off and Landing of the Supersonic Transport
Authors: Greatrex F.B.
Published: November 2014

The author was asked to prepare this paper for a discussion on take‐off and landing noise problems on the supersonic transport at a Symposium at Southampton University. He was in the fortunate position of being sufficiently detached from direct participation in the project that he did not need to be hampered too much by hard facts—he could hope to keep the interest of his audience by raising general problems and discussing methods of solution without specifying what the actual solutions were going to be. After all there is nothing more inhibiting to a good lunch‐table conversation than the presence of someone who actually knows the answers to the problems under discussion.
Concord Progress
Authors: Edwards George
Published: November 2014

Originally, this article took the form of the Twenty‐first Brancker Memorial Lecture delivered to a meeting of The Institute of Transport. The author began his lecture by saying how honoured he was by the invitation to present the 1964 Brancker Memorial Lecture and that he felt especially privileged to have the opportunity of surveying a prospect which he believed would have excited Sir Sefton Brancker's most ardent enthusiasm—the prospect of reducing inter‐continental journey times‐by air to the same durations as those universally accepted for inter‐city journeys by rail and road. Previous Brancker Memorial Lectures had summarized the general development of British civil aviation from its earliest days to 1946 and had covered particular aspects of its very rapid expansion since that date. 1946 was a significant year because it marked the resurgence of commercial flying after seven years of wartime restrictions and regulation; it promised a new deal to both operators and travelling public, with the opportunity of usefully applying technical advances achieved during the war period; at the same time it threw into sharp contrast the relative design capabilities of the British and American aircraft manufacturing industries.
Comparative Performance of Five Chipmunk Aircraft
Authors: Fawcett J.H.
Published: November 2014

The intention of this paper is to compare the performance of five Chipmunk aircraft, and to investigate the assumption that the performance of any operational aircraft can be considered to be representative of that type of aircraft. All the aircraft were tested, with the same instrument panel fitted, and were weighed in order to determine the variation in weight and centre of gravity. Flight tests were then conducted to investigate the following aspects of performance: turning, climbing, drag, engine power, stalling and spinning. The results, reduced from the readings taken during flight tests, showed that there are two main causes of variation between the performances of the aircraft. First the age and condition of the engine were seen to affect the power dependent aspects of performance. Secondly there was a wide variation of profile drag which was probably due to distortion of the airframes.
Development of Strong Aluminium Alloys
Authors: Doyle W.M.
Published: November 2014

A Description of the Facilities Available in the Research Division of High Duty Alloys Ltd. and an Account of the Work Carried Out in Developing the Hiduminium‐RR.58 Alloy which has been Specified for the Anglo‐French Concord Supersonic Airliner. A brief account of the research work necessary for the development of aluminium alloys with special properties, in particular Hiduminium‐RR.58, the alloy which was initiated and developed by Dr W. M. Doyle and his colleagues and has now been specified by both the British and French designers for the construction of the B.A.C./Sud Concord supersonic airliner.
Refuelling in Flight
Authors: Macgregor P.S.
Published: November 2014

EVER since the inception of the hcavier‐than‐air flying machine, the need to refuel in flight has been apparent. The cartoon reproduced in fig. 1 was first published in Punch in 1909, at a time when the payload of the aeroplane was very small, due to the large tare weight of the airframe and engine. Present day aircraft have a much higher payload capability, in relation to tare weight, but it is still necessary to carry the energy for propulsion within the aircraft, with the result that long range can only be achieved at the expense of payload. The propulsion energy in orthodox aircraft has always been carried in the form of hydrocarbon fucls,bccause of their ready availability, high calorific value per pound weight and high calorific value per cubic foot. Work has been in progress for some years to develop solid fuel conversion, in the interests of saving weight and space, but such fuels are likely to be extremely expensive and potentially dangerous to handle. However, the problem remains that a consumable fuel source must be carried in the aircraft, with consequent reduction of payload or range. The use of nuclear engines for aircraft has been contemplated, but it seems probable that the weight of shielding and coolant, associated with this type of engine, will limit its use to very large aircraft.
Structural Design Part I—Basic Design
Authors: Ashley H.R.
Published: November 2014

The Basic Design Philosophy as it Applies to all Load‐Carrying Elements including a Description of Fuel Tank Design, Flap Structure and Floor Layout. FROM the structural viewpoint the aircraft had to suit the needs of the small or medium‐sized airline having difficult operating conditions. Structural integrity would have to be maintained with limited servicing facilities and the aircraft must be capable of operating in remote areas from rough airstrips. Therefore, this meant that the aircraft had to have a high degree of reliability and serviceability, be of rugged construction with a long fatigue life, be designed for easy maintenance on a scheduled inspection basis, and have quick turn round times using the minimum of staff and facilities.
Efficiency in Reading
Authors: Wainwright G.R.
Published: November 2014

A Brief Review of the Advantages of Being Able to Read More Quickly, Some Proposals for Improving Reading Efficiency and the Results of Some Reading Efficiency Courses held at Hull College of Technology. Many engineers and executives in the aerospace industry have more reading to do than they can cope with efficiently in the time available to them. There are a number of reasons for slow rate of reading but it does seem to be possible for most readers to double their reading speed, with training and practice, without loss of comprehension. In fact comprehension may well improve in the process. Some methods of acquiring the skills of efficient reading are suggested.
The Development of a Torsional Vibration Computer
Authors: Morton A.S.
Published: November 2014

This paper describes the development of a torsional vibration computer for the determination of the natural frequencies of torsional oscillations. Although a five mass system is used as an example of the proposed method the technique can be used with systems having any number of masses. Experimental results showed that the accuracy obtained with the computer was good.
B.A.C. One‐Eleven Interior Furnishing Engineering
Authors: Barfield N.A.
Published: November 2014

A review of the design philosophy, primary design features and management of airline and executive customer variants, followed by a description of furnishing materials, fixed trim assembly, passengers' personal item stowages and facilities, lighting, cabin staff appointments and communication, catering installations, toilets, domestic water system and emergency provisions.
The Prospects for Civil V.T.O.L. Aircraft
Authors: Chichester‐Miles Ian
Published: November 2014

AT the present time, with preparations in hand for the advent of the supersonic transport aircraft, it is a sobering thought that the fastest overall journey speed between the centres of London and Paris is of the order of 80 m.p.h. Despite the relatively high standard of comfort offered by the modern airliner over short stages its main attraction—speed—is being rivalled by the high speed train and its greatest competition is still the motor car.
Improvement in Ground Service Equipment
Authors: Fuell F.J.
Published: November 2014

ONE of the most fortunate factors in hydraulic oil filtration is that in recent years the manufacturers and users have recognized its genuine importance. The need for constant improvement in the standard of cleanliness of hydraulic oils has resulted from increased sophistication of the system concerned, and has certainly posed problems for the manufacturers of filtration equipment.
Designing to Combat Fatigue
Authors: McElhinney D.M.
Published: November 2014

THE increasingly competitive nature of both the operational and manufacturing sides of the aviation business has had the effect of making the designer more conscious of the economic characteristics which he is building into his aircraft, and these have now become a major design consideration.