bluuebunny/crossref_metadata_2025 huggingface dataset:
Aeroelastic Problems of Low Aspect Ratio Wings
Authors: Farbridge J.E.F. , Woodward F.A. , Thomann G.E.A.
Published: February 2008

This final paper of the series deals with the application of the structural and aerodynamic matrices to determine the final steady state loading on the wing, with a view to the requirements of the stress analyst. It is also shown how the stability derivatives of the elastic wing may be obtained, if a system of unit loads is employed in the calculations. Finally the occurrence of wing divergence and control surface reversal speeds are discussed in the light of the proposed methods.
Pressure Distribution and Aerodynamic Properties of High‐Speed Aircraft
Authors: Pivko Svetopolk
Published: February 2008

Using the results of earlier investigations, a method for determination of the velocity or pressure distribution and the aerodynamic properties of a low‐aspect‐ratio swept wing with slender body of elliptical cross‐section and vertical tail surface, having arbtrary form, is briefly presented. The method can be used for the prediction of the load distribution, aerodynamic forces and moments on inclined slender wing, body and vertical tail combinations travelling at subsonic or supersonic speeds.
Gas Flow and Units
Authors: Naylor V.D.
Published: February 2008

WHEN dealing with questions on gas flow, a certain amount of visual simplification in the resulting equations is produced by using the reservoir conditions as our unitary system.
Fundamental Flow Patterns
Authors: Brown F.N.M.
Published: February 2008

THE accompanying flow pictures arc selected from those used to illustrate the lecturer's notes in a course dealing with viscous fluids. The use of the pictures saves an astonishing amount of lecture time in those categories of study where the real flow patterns agree reasonably with the classical rationalized concepts. This time is profitably used in those regions of sharp departure of the real pattern from the classical concepts: in boundary layer transition, in leading edge separation with subsequent rejoining, in the mechanism of circulation growth accompanying rapid change of angle of attack, in wake survey for drag determination and in many others.
The Buckling of Tapered Plates in Compression
Authors: Klein Bertram
Published: February 2008

A simple matric formulation is developed for calculating the elastic buckling of a class of simply supported flat plates that arc simultaneously tapered in plan form and in thickness in one direction and subjected to biaxial loading that varies in each direction. Design curves are presented for the special case when the thickness taper is linear and the plate material is equally stressed in the direction of this thickness taper.
Perturbations of a Body in an Exponential Atmosphere
Authors: Cuming H.G.
Published: February 2008

THE purpose of this note is to derive an analytic solution to the second order linear differential equation whose coefficients vary exponentially with time. Such equations arise in the investigation of small perturbations in the linear motion of a body through the atmosphere in which the density may be considered to vary exponentially with height. For example, if the perturbation considered be a small angle of incidence of the body to the direction of the undisturbed motion and the velocity of descent is taken to be constant, then with linearized aero‐dynamics both the restoring and damping moments are proportional to the atmospheric density and therefore vary exponentially with height and hence with time. For sufficiently slow time rates of variation in the coefficients an iterative solution may be obtained in the form of an infinite series. The difficulty inherent in this method lies in determining the convergence of the scries obtained. Apart from this, the method fails in the topically interesting case of rapid descent where the coefficients vary rapidly with time. The following method overcomes this difficulty and leads to a solution valid over the whole range of descent velocity, provided only that the motion due to perturbation is lightly damped, a condition usually satisfied in practical cases.
Productivity in the Wartime Aircraft Industry
Authors: Broster E.J.
Published: February 2008

WHEN the Ministry of Aircraft Production drastically reduced the military aircraft programme in 1945, forecasts had to be made of the consequential reductions in labour requirements in the aircraft factories. During the drawn‐out build‐up period, and the period of relative stability in 1944, labour forecasts had been made with somewhat arbitrary adjustments, and not entirely without success, on a pro rata basis. With the end of the war in sight, the forecasters were faced with a programme that showed a reduction of something like 75 per cent in output to be achieved in the course of a few months. Could the pro rata assumption give labour forecasts even approaching the right order of magnitude?
Problems of Machining Future Airframes
Authors: Famme J.H.
Published: February 2008

THERE has been considerable discussion in the industry concerning the various barriers facing aircraft designers. We hear about such things as the sound barrier, the heat barrier and the space barrier.
Helicopter Longitudinal Stability
Authors: Payne P.R.
Published: February 2008

CONSIDER a single rotor helicopter disturbed from the hovering condition as in FIG. 16. It has acquired a small forward velocity V ft./sec. and a nose‐up angular velocity of q rads./sec. For simplicity we consider the centre of gravity of the fuselage to be on the shaft axis, since its actual position can be shown to have a negligible effect in hovering. Resolving moments about the centre of gravity, the important terms are
Stress in a Curved Skin Panel of a Pressurized Fuselage
Authors: Lockwood Taylor J.
Published: February 2008

The problem solved is that of an initially curved circumferential skin strip, representing a section of the panel midway between frames, continuous over the stringers which act as sinking supports and transfer part of the internal pressure load to the frames. The remainder of the pressure load produces hoop tension in the skin strip, but the maximum total stress including bending in the skin at the stringer, which is evaluated, is usually greater than would arise from hoop tension alone, in an unstiffened shell.
Energy Limitations of Liquid Rocket Propellants
Authors: Tormey John F.
Published: February 2008

APPLICATION of the so‐called high energy liquid fuels and high energy liquid oxidizers to power plants based on the jet propulsion principle is receiving the increasing interest and attention of rocket propellant chemists and power plant engineers universally. The aspect of substantially increased—as much as 50 per cent— energy per pound of propellant load or per cubic foot of propellant tankage over today's propellants has whetted scientific appetites and justified probing the field of high energy chemicals to determine, as logically and as practically as we can at the present time, the gains, problems, limitations and applications of these higher energy chemicals. The object of this paper is, in a general way, to discuss the subject of chemical rocket propellants in such a way that the following five questions will be, in part at least, answered or recalled to the minds of this audience for additional deliberation.
Some Effects of Kinetic Heating on the Stiffness of Thin Wings
Authors: Kochanski S.L. , Argyris J.H.
Published: February 2008

This paper presents a preliminary analysis of the effects of kinetic healing at supersonic speeds on the torsional and flexural stiffnesses of thin solid wings. The main investigation is based on the small deflexion theory, but the scope of the analysis for torsion is extended to cover the effects of large deformations.
Dynamic Similarity
Authors: Coward Ken S.
Published: February 2008

WITH the advent of VTOL aircraft, dynamic similarity has become increasingly important. VTOL performance is dependent upon propeller diameter or upon the cross‐sectional area of a jet stream. Without understanding the effects of dynamic similarity, propeller ratings in thrust per horse‐power may be misleading as a design criterion in equating aircraft size to a desired mission.
The Impact of Bearing Clearances on Shaft Stability
Authors: Morris J.
Published: February 2008

It is shown that the clearances between the journals of a shaft and the bearings in which it runs may give rise to a species of unbalance and that unless this unbalance is corrected by a counter unbalance in the shaft or loads carried by it, steady motion is impossible in certain ranges of speed. The treatment presented is concerned with conditions for steady circular motion rather than with transient disturbances.
Ultra‐Violet and White Lighting for Aircraft Instruments
Authors: Chittenden P.
Published: February 2008

THE aircraft industry is always trying to improve cockpit lighting, and over the years many different arrangements of tungsten filament lamp have been used. Red lighting has long been standard equipment for aircraft and, during the last twenty years, ultra‐violet lighting with Woods glass tungsten lamps has been very successful.
Some Effects of Kinetic Heating on the Stiffness of Thin Wings‐II
Authors: Kochanski S.L. , Argyris J.H.
Published: February 2008

THIS Appendix summarizes an investigation of the elastic characteristics of thin singly symmetrical parabolic wings with small initial parabolic camber subjected to non‐linear temperature gradients and large spanwise curvature and twist.
The Library Shelf
Authors: S.L.K.  , E.G.B.
Published: February 2008

This book is an important study of the clastic behaviour of thin wings subjected to non‐linear temperature gradients and particularly valuable are the numerous experimental results which confirm, in general, the theoretical predictions. The analysis, developed from the shallow shell theory of Marguerre, is confined to wings of infinite aspect ratio.
Ninth International Astronautical Congress
Authors: Thompson G.Y.E.
Published: February 2008

Author's preference for use of term magnetofluidmechanics instead of magnctohydromechanics; résumé of main principles; applications of the science in astronautics.
Characteristics of Slender Wing‐Body Combinations with Folding Wings
Authors: Campbell George S.
Published: February 2008

A method has been developed for computing aerodynamic loads on slender missiles with complicated cross‐sections. This method has been applied to the prediction of loads for missiles with folding wings. Comparison of theoretical calculations with supersonic wind‐tunnel measurements indicates that the method should provide satisfactory first estimates of the aerodynamic properties of missiles with folding wings. A series of design charts is presented to allow rapid estimation of lift, folding moment and span loading for a wide variety of folding‐wing configurations.
Induced Flow Near a Helicopter Rotor
Authors: Heyson Harry H.
Published: February 2008

The basis and the extent of theoretical induced velocity calculations are reviewed. The theory is then applied to interference problems involving additional rotors, wings, and tails in the flow. For such cases, the interference effects can be calculated with acceptable accuracy. For hovering, superposition is used to introduce ground effect into the calculations. The resulting flow field offers a qualitative explanation of several previously observed phenomena. It is shown that, because of assumptions inherent in the analysis, the present induced‐flow theory cannot be used to predict the detailed aerodynamic loading on the rotor blades.
Impact Sensitivity of Organic Materials on Exposure to Liquid Oxygen
Authors: Clippinger D.E. , Morris G.J.
Published: February 2008

THE use of liquid oxygen as an oxidizer for various fuels in liquid rocket propellent systems is not new. Professor Goddard used liquid oxygen in his rocket experiments and the well known German V‐2 rockets used this material as an oxidizer. However, its effect on non‐metallic materials ordinarily used in rocket systems was not investigated until recent years. This investigation was prompted by phenomena which had been experienced by rocket engine and rocket aircraft manufacturers and by suppliers of the material. It was observed that when some organic materials came in intimate contact with liquid oxygen they became prone to detonation when subjected to certain impact energies. This was undoubtedly due to the formation of unstable organo‐peroxide compounds which when impacted released high levels of energy resulting in an explosion. Specifically, when liquid oxygen was accidently spilled on asphalt and inadvertently stepped on, the asphalt would often explode. Also, leather gaskets immersed in liquid oxygen and subjected to surge impact detonated with disastrous effects.
Anti‐Vibration Mounting of Aircraft Power Plants
Authors: Harriman J.F.
Published: February 2008

UPON completion of the design for the engine mounting it is most desirable that some ground testing should be carried out before the mounting is flight tested. These tests will provide information on the mounting resonances and modes of vibration, deflexions of the engine and mounting under load and they may also be extended to include proof and ultimate load tests for various critical flight cases. The degree of vibration isolation achieved can also be estimated bearing in mind the differences in suspension on the test beds compared with the actual aeroplane and any changes found to be necessary can be incorporated and tested more readily on the ground than in the air.
Solution of Modified Linear Simultaneous Equations
Authors: Goodey W.J.
Published: February 2008

A PROBLEM arises in the matrix analysis of highly redundant structures, and no doubt often occurs in other engineering and scientific contexts, in which a set of linear simultaneous equations, which has already been solved for one particular set of values of the coefficients, has to be solved again when some of the coefficients are altered. In the structural context the problem is to find the effect of altering the sizes of some of the members of a structure. This alters the matrix of coefficients of the equations for the unknowns (the redundancies) in a rather special way, but in other problems the alterations in the matrix may be of a more general character. It was accordingly decided to investigate the general problem of matrix modification to sec if some method could be devised which did not involve the complete solution of the altered equations ab initio, but which made use of the work already done in solving the original equations. It seemed reasonable to suppose that the amount of work involved in finding the solution of the modified equations could be related to the number of altered coefficients, so that if only a few of the coefficients were altered the amount of additional work to obtain the new solution would be correspondingly small.
Tenth International Astronautical Congress
Authors: Thompson G.V.E.
Published: February 2008

The present stage of development of vehicles for space exploration corresponds to some degree to that of the aeroplane in 1905. The programme of the U.S. National Aeronautics and Space Administration in the fields of space science research, applications of Earth satellites, manned exploration of space, and vehicle development are reviewed. International co‐operation in space exploration is desirable, particularly as regards exchange of information, exchanges of scientists, co‐ordination of national programmes, and institution of co‐operative programmes.
High Energy Forming
Authors: Carpenter S.R.
Published: February 2008

Machine tools have been developed to produce high energy levels at high rates. It has been discovered that metals exhibit hydrodynamic properties, when subjected to these conditions, which facilitate shaping. The principle has been applied to the shaping of steel tungsten, columbium, sintered nickel and other metals. Thin sections may be extruded and forged and the effect on cost reduction is substantial.
Fatigue Fracture
Authors: Forsyth P.J.E. , Ryder D.A.
Published: February 2008

IN 1950 Zapffe and Worden used the metal‐lurgical microscope for the examination of fatigue fracture surfaces, a technique which they called fractography. They suggested, as a result of their observations, that fatigue fractures showed two characteristics:
Fatigue Resistance
Authors: Smith C.R.
Published: February 2008

Contrary to the general conception of adding weight for fatigue resistance it is sometimes possible to reduce the fatigue hazard by removing weight. The theory of having bearing area, tear‐out area, and tension area sufficient to develop the full shear strength of a rivet is not necessarily sound when fatigue life is considered. Accordingly, marked improvements in fatigue resistance can be achieved by reducing the underlying areas to such an extent that they are incapable of inducing loads causing fatigue failures of the main structure. Results of tests involving fatigue failure are given, and seven basic considerations in the design of fatigue resistant structures are listed.
The Library Shelf
Authors: A.D.B.  , A.J.K.
Published: February 2008

The AGARD series of books are now becoming well established as valuable contributions to the technical literature on aeronautics. The present book adds one more volume and some considerable support to the reputation of the series. It consists primarily of papers presented at a joint meeting of the Combustion and Propulsion and the Wind Tunnel and Model Testing Panels of AGARD. The object of the meeting was to review the recent developments in ground test facilities and their applications to engine design and development and to compare them with inflight testing.
Solid Propellent Burning Rate Theory
Authors: Gutman V.R.
Published: February 2008

The progress of solid propellent technology appears to have been retarded by lack of development of a fundamental mechanism of burning. A study of previous work indicates that while experimental techniques used are valid, hypotheses were inadequate; and fresh hypothetical approaches are needed. There is evidence of lack of theory development in the more fundamental field of the combustion of turbulent, pre‐mixed, fuel‐rich flames as it applies to propellent burning. The roles of radiative heat transfer and a physical disintegrative mode of surface dissipation are proposed for consideration. Previous experimental techniques together with new ones are proposed to exploit these hypotheses.
Effect of Fixed Forward Fins!
Authors: Campbell G.S.
Published: February 2008

An estimate is made of the effect of adding a small forward fin on the lift and centre of pressure of a slender wing‐body combination. The fin is assumed to discharge a trailing vortex which interacts with the main lifting surface. Design charts permit rapid estimation of lift loss and centre of pressure movement for a delta wing plus body. At the lower angles of attack, the lift loss on the wing is approximately equal to the lift of the forward surface itself. Most of the lift is lost at the front of the wing, and so wing centre of pressure moves aft with addition of the forward fin. Theoretical estimates are in general agreement with experimental results at Mach numbers 1·65 and 2·41.
The Analysis of Fuselages of Arbitrary Cross‐section and Taper
Authors: Argyris J.H. , Kelsey S.
Published: February 2008

The general theory of the cut‐out and modification analysis is reviewed and extended for a structure involving primary, secondary and tertiary redundancies. Some important points of practical application are illustrated on simple examples and the influence of the form chosen for the unassembled flexibility matrix is discussed. The question of the selection and number of actual cuts which will simulate a given major cut‐out is treated in general and illustrated on a simple type of structure.
The Analysis of Fuselages of Arbitrary Cross‐section and Taper
Authors: Argyris J.H. , Kelsey S.
Published: February 2008

As a first example of the application of the cut‐out procedure to fuselage problems and the selection of appropriate cut systems, the elimination of a complete ring is discussed in detail. ‘Minimal’, ‘maximal’ and ‘dismembering’ techniques are all applied to singly and doubly connected rings, and attention is drawn to some inadmissible and critical combinations of cuts in order to guide the most effective choice. The second fuselage example treats similarly the removal of a portion only of the ring.
The Analysis of Fuselages of Arbitrary Cross‐section and Taper
Authors: Argyris J.H. , Kelsey S.
Published: February 2008

In the two short sections which close Chapter VII, an improved ring programme is developed which allows i.a. for the application of externally applied moments on the ring vertices and a preliminary and tentative extension of the analysis takes into account the bending stiffness of some of the flanges. The final chapter returns to the subject of the uniform, circular section fuselage and develops the theory for the polygonized cross‐section in analytical form. Standard expressions are given for the elements of the D,, matrix and application of the analysis to a simple example suggests that the effect of the polygonization on the accuracy of the stress distribution is insignificant.
Engines for Supersonic Civil Transport Aircraft
Authors: Keenan J.G.
Published: February 2008

Because of its high overall pressure ratio and good propulsive efficiency, the jet engine is very efficient for supersonic propulsion. A high thrust per unit power plant frontal area and per unit weight are primary requirements and these imply high combustion temperatures. For a Mach 2.0 aircraft, engine design problems other than this are not outside existing experience but additional problems, such as bearing cooling, become more serious at cruise Mach Numbers approaching 3.0. A variable intake is essential and the method of geometry variation and control requirements are described. Variable propulsion nozzle design is also an area of vital importance and it is not claimed that an entirely satisfactory solution, giving good performance with low drag in the transonic phase, has yet been achieved. The ‘sonic boom’ phenomenon can have an important influence on engine design, in that it may determine the maximum altitude at which the aircraft has to fly subsonically. Should this be appreciably above the tropopause, then it will not only influence the amount of thrust installed but may also dictate the fitment of reheat for the transonic acceleration. Take‐off noise is a requirement which can influence both the installed thrust and the choice of engine type. Despite the lack of firm standards for field noise and ‘coast‐over’ noise, there is good reason to believe that the noise levels of a supersonic transport need not exceed those of the quieter long‐range subsonic transports in service at this time.
Part Two‐Applied Aerodynamics A Review of Recent Progress and Problems Associated with the Subsonic, Transonic, Supersonic and Hypersonic Speed Regimes
Authors: Hamilton J.C.
Published: February 2008

DURING the first forty years or so of the history of manned flight, the application of aerodynamics was confined largely to subsonic speeds and to one basic aircraft shape. Since the end of the Second World War the aerodynamic domain has expanded in spectacular fashion in terms of speed and shape until at the present time ‘conventional’ manned aircraft are penetrating into the realms of hypersonic velocities and the satellite vehicle has brought with it aerodynamic problems at what must surely be the near‐ultimate speed range for the technology. Nor are these advances confined to high‐speed aerodynamics: they include radically new approaches to low‐speed problems, particularly those arising from take‐off and landing manoeuvres.
Crack Propagation
Authors: Schijve J. , Broek D.
Published: February 2008

This paper deals with crack propagation under programme‐fatigue loading; the programme being derived from a gust spectrum. The validity of the Palmgren‐Miner rule for crack propagation has been studied and its usefulness for design purposes is discussed.
The Hawker P. 1127/Bristol Siddeley Pegasus Combination
Authors: Frost T.P.
Published: February 2008

THE increased mobility of modern warfare, combined with the rapid advance in the destructive power of the weapons available, requires that military aircraft should become increasingly independent of conventional bases with their ‘Maginot Line’ vulnerability. Therefore, the ability to operate from any surface anywhere, be it jungle clearing or city out‐skirts, must be an essential feature of future tactical strike reconnaissance aircraft. This can be provided by the incorporation of a V/S.T.O.L. capability. In addition, simplicity and general robustness arc essential, since the present trend for increasingly sophisticated systems, requiring highly trained specialists and complicated servicing equipment, imposes an. unacceptable restriction when operating in a fluid battle area.
Today and Tomorrow
Authors: Bellworthy A.J.
Published: February 2008

AERONAUTICAL engineers are constantly seeking materials with high strength/low weight ratios, particularly those who are associated with commercial aircraft design where this aspect is vital, since payload is directly related to economical airline operation.
Testing of Reinforced Plastics at Elevated Temperatures
Authors: Denney M.A. , Martindale J.C.
Published: February 2008

WITH the development of supersonic aircraft there is an increasing requirement for structural materials operating at elevated temperatures. To ensure optimum utilization of reinforced plastics it is essential to provide the designer with accurate data on performance at these temperatures.
Design Philosophy and Structural Details
Authors: Goodwin C.J.
Published: February 2008

THE launching of a new aircraft in this highly competitive age is a very expensive undertaking —and as a result, a risky one. If a new or growing demand can be satisfied by the further development of an existing type then the risk will be reduced and the reward increased so that a commercially successful aircraft is almost invariably in production for many years and progressively developed through a number of versions. However, the law of diminishing returns operates and eventually the time must come when it is necessary to recognize the fact that a new aircraft promises equal if not greater returns than continued development of the older aircraft, despite the expense associated with commencing and producing a new type.
Electrically‐Suspended Gyros
Authors: Riesgraf M.H.
Published: February 2008

SIGNIFICANT strides have been made in the development of advanced electrically‐suspended inertial components and systems capable of utilizing them. At Honeywell, considerable contract support by both the United States Navy and the United States Air Force, in addition to Company‐sponsored effort, has resulted in Electrically‐Suspended Gyros that have achieved accuracies of one or two orders of magnitude better than those of the best conventional gyros.
Power for the Concord
Authors: Frost T.P. , Little J.P.
Published: February 2008

THE power plant for the Concord supersonic transport has evolved from an optimization study which showed that a medium‐pressure ratio turbojet would be the best compromise for a transatlantic M=2•2 civil aircraft. The detail design of the engine intake and nozzle systems is currently proceeding in the Design Offices of British Aircraft Corporation and Bristol Siddeley Engines in England and S.N.E.C.M.A. in France.
Dye Penetrant Techniques for Flaw Detection
Authors: Grizzell G.A.
Published: February 2008

FLAW detection processes utilizing dye penetrants are now extensively used throughout the aircraft industry. They are a logical development of the lard oil and chalk method popular in the early days, a system which is still occasionally used for economic reasons and where only the more obvious flaws are of significance. Briefly, this method consists of immersing the parts to be tested in hot lard oil, wiping off the excess, and then applying a film of chalk; oil which has seeped into surface flaws eventually exudes out and is absorbed into the chalk, revealing itself as typical oily stains. It was reasoned that if lard oil were substituted by a penetrating medium which was highly coloured, the exudations would then become much more obvious and from then on intensive research programmes were started which have culminated in the very efficient processes now available.
Aero engine‐finishes
Authors: Butler C. , Cork F.
Published: February 2008

Progress Made by the Laboratories of Rolls‐Royce Ltd. and Robert Kearsley & Co. in the Formulation and Manufacture of Surface Coatings and the Techniques Used in Applying these Coatings to Aircraft Engines
Progress with the Development of the B.A.C. One‐Eleven
Authors: Prothero Thomas J.
Published: February 2008

THE development of an airliner is an extremely complex operation calling for many different professional skills and a vast amount of testing and development facilities.
The Engine's Contribution to Economic Short‐Haul Jet Transport
Authors: Eltis E.M. , Morley F.W.
Published: February 2008

Improvements in Engine and Power Plant including Reduction in Fuel Consumption, Mechanical Design, Blade Cooling, Lower Vibration, Foreign Object Damage, Oil Consumption, and Reduction in Overhaul Life, all of which can Contribute in Significant Manner to Lower Operating Costs. Recent engine improvements to reduce operating costs are discussed, including examples of features ensuring low vibration level, low metal temperatures of hot end parts, etc. It is predicted that modern techniques will make more major components capable of lasting the whole life span of the engine, facilitating the replacement of present overhaul procedure by sectional overhaul. A possible way to reduce power plant weight is referred to. It is concluded that further advances towards higher engine performance will be accompanied by economies in many other areas of the power unit.
Test Methods to Establish Strength and Reliability
Authors: Taylor P.W.
Published: February 2008

Three main subjects are presented in this paper: (i) A description of tests made for the purpose of determining design data; (ii) a discussion of the problems arising in the establishment of the approval procedures necessary to ensure safety and reliability; and (iii) a discussion of proposals for cyclic reliability tests. In the first section, tests to provide design data for glazing materials are described with particular emphasis placed on glasses. Types of specimen and apparatus for obtaining data at room temperature are mentioned and illustrations given of apparatus and specimens used in long term elevated temperature tests. In the second section, the overall level of reliability of complete components is discussed both in terms of structural safety and satisfactory service. While the current requirements have proved satisfactory for the past generation of aircraft, proposals are now put forward for patterns of testing that are more closely linked to the various design conditions now in use with both high‐speed and low‐speed aircraft, in order to place equal importance on the effects of temperature. In the third section, proposals are put forward for cyclic testing to overcome what appears to be an increasingly unsatisfactory record of reliability. The purpose of the tests is not to establish a safe life for any particular design but to reveal design deficiencies occurring from repeated applications of flight and thermal loadings.
Factors Affecting Stress Formation in Glass During the Toughening Process
Authors: Beattie J.R.
Published: February 2008

The mechanism of stress formation in glass under‐going conditions of rapid cooling, and the factors affecting the properties of the toughened glass produced are discussed. The application of techniques for measuring the temperature of glass, to the control and study of the toughening process are described.
The Resistance of Transparencies to Bird Impact at High Speeds
Authors: McNaughtan I.I.
Published: February 2008

The methods of bird impact testing or aircraft transparencies are discussed and a review is made of tests on aircraft transparencies and transparency materials. The review includes the effects of temperature, of mounting and of the use of compound material screens. The validity of present design parameters are examined and proposals on both design parameters and test methods are presented.
Power Plant
Authors: Barrett J.A.
Published: February 2008

TWENTY‐FIVE years ago, the gas turbine was successfully applied to aircraft propulsion for the first time and it was not long after this event that powerful engines of reasonable efficiency appeared. In strong contrast with the early success of large engines, the evolution of equally efficient small engines has proved both difficult and protracted. That few of the major manufacturers have persisted with their development may be surprising but is also indicative of the technical problems involved. Thus it reflects great credit upon Turboméca that they have produced the first turbines to offer a serious challenge to piston engines for small aircraft installations. In this connection, the Astazou occupies a significant position as the first small propeller turbine to achieve any real measure of success, and it has been developed progressively to maintain its early lead over competitors. Consequently this engine was the obvious choice to power the Turbo‐Skyvan.
The Boeing Variable‐Sweep Supersonic Transport
Authors: Swihart J.M. , Goodman L T.
Published: February 2008

This paper describes the principal features of the Boeing variable‐sweep supersonic transport and compares the aircraft's performance with that of the low aspect ratio supersonic transport. It is important to note that where comparisons are made between the Boeing 733 SST and the BAC‐Sud Concorde, the performance of the American airliner relates to the earliest version of the aircraft (a process of design refinement is continuing and the final form of the aircraft is therefore not jet decided) while the characteristics of the Anglo‐French airliner are based on those of the small early version of the aircraft—the latest version being of much larger wing area, having higher thrust engines and generally improved design features (see ‘Concorde— Interim Report’, Aircraft Engineering, July 1965, pp. 218–24)—Editor.
Application of Supersonic Combustion to Ramjets
Authors: Viaud Louis , Mestre André
Published: February 2008

THE interest shown lately in ramjet‐type engines for propulsion of hypersonic vehicles within the atmosphere has led us to consider using supersonic combustion ramjets, also called scramjets. It appears that this type of combustion is mandatory when the flight Mach number is of the order of 12.
Flight Deck Display for Future Aircraft Projects
Authors: Brown Milton
Published: February 2008

IN the U.S. today there is a heavy emphasis on cockpit instrument display development due to several new F.A.A. Advisory Circulars, the most important of which spell out the requirements for Category 11 approval.
The West German Aircraft Industry
Authors: Dudley R.P.
Published: February 2008

A LATE take‐off, compared with other countries, has not stopped West Germany's aircraft industry from reaching for the heights. Prevented from making an early start by the Allies after the last war, the German aircraft manufacturers had to stand and watch its national airline, Deutsche Lufthansa, starting up again without being able to supply any aircraft for its use. Production of parts and later of whole aircraft only got off the ground under N.A.T.O. shields and through licensing schemes from foreign companies. German engineers had a long backlog to make up, both in skills and in experience and know‐how, but they eventually overcame those obstacles. They were helped by their friends who lad previously granted them production licences and encouraged by their Government to amalgamate into larger units. The latter was achieved more or less on a geographic basis: two loosely woven sets of co‐operative groups were created, one in the North and the other in the South of the country, named respectively Entwicklungsring Süd and Entwicklungsring Nord. Each component company maintains its own identity and is still able to continue its own research or production work or to look for partners for specific schemes in other countries.
The Ignition of Inflammable Fluids by Hot Surfaces
Authors: Goodall D.G. , Ingle R.
Published: February 2008

IN recent years, much attention has been given to spontaneous ignition problems because of the high skin temperatures of aircraft operating at high Mach numbers. The problem is not really new, however, since for many years aircraft engines have been operating with carcase temperatures above the laboratory closed vessel spontaneous ignition temperatures for fuels and lubricants, and installation engineers have collected a good deal of ad hoc data to justify the safety of particular power plants. FIG. 1 indicates the main risk areas for a typical subsonic by‐pass jet installation.
Wind Tunnel Test on Models of V.T.O. Aircraft
Authors: Emslie K.
Published: February 2008

A straight through wind tunnel sited outdoors was completed in 1963. A 200 h.p. diesel engine gives 75 ft./sec. in the 18‐ft. square section. Models small enough to avoid serious wall constraint are tested statically with fully simulated lift systems to measure the performance and handling characteristics of V.T.O. aircraft at low forward speeds. Intake and jet flows are induced by ejector pumps which occupy representative positions in the engine bay. Engines and airframe are mounted separately to measure loads on tailored balances, and surfaces are extensively pressure plotted. Thus aerodynamic interferences are isolated, giving the physical back‐ground for the formulation of theoretical treatments and calculation methods, involving jet mixing regions and separated flows. Meanwhile empirical data is available for early design work to develop V.T.O. aircraft with useful payload and range. Configurations which minimize the download due to ground effect tend to develop large downloads during the transition manoeuvre. The worst configurations suffer nearly complete loss of the installed vertical thrust, due to aerodynamic interferences on the airframe. Moderate overloading of a V.T.O. aircraft with poor transition performance results in a long take‐off run.
The Birth of Beagle
Authors: Greenhalgh A.J.
Published: February 2008

THE United Kingdom pioneered the practical light aircraft in the 1920s and continued to be one of its major producers and exporters until the early 1950s. More than 15 years ago, however, as a result of the Royal Air Force decision to use jet aircraft for training its pilots, and because the bigger British aircraft manufacturers were becoming entirely preoccupied with large and complicated high performance military and civil aircraft, which in turn led to these companies being consolidated into large groups, the British development of light aircraft practically ceased. Production of such aircraft had in fact almost entirely stoppped by the late 1950s. This represented a grave loss to British exports in a world market worth more than £80,000,000 a year, and it had a serious effect on the prestige and competitive strength of this country's aircraft industry as a whole.
Power Plant and Aircraft Systems
Authors: Guest R.F.W.
Published: February 2008

BECAUSE of relatively high power to weight factor, general compactness with low frontal area, competitive specific fuel consumption and general ruggedness, the horizontally opposed engines manufactured by Continental Motors Corporation have been used by small aircraft over the past twenty‐five years. The manufacture of the four and six cylinder versions of these engines has been undertaken by the Rolls‐Royce Ltd, who have participated with Beagle in providing a sophisticated installation on the B.206 aircraft.
Flight Trials and Testing
Authors: Judge J.W.C. , Cummings D.
Published: February 2008

SINGLE pilot operation with one or two observers, depending on the work to be done, has been adopted for all test flying. Required loadings are achieved by adjusting fuel quantity and lead ballast. The observer is positioned aft of the pilot where he can scan all the pilots' flight and engine instruments and also monitor an observer panel mounted behind the second pilot's scat and facing inboard (FIG. 1). The other observer is in the second pilot's scat where he has a parallax‐free view of the engine and starboard flight instruments. Thus for performance flying the forward observer has all the basic instruments within a narrow are whilst the aft observer can concentrate on special pressure and temperature instrumentation on the test panel, the two sets of readings being co‐related during performance climbs by time and altitude.
Production and Assembly
Authors: Bellamy E.M.
Published: February 2008

A MAJOR problem associated with the production of light aircraft is the ability to feed individual customer requirements into the build stages with a minimum amount of retrospective work. Orders for a number of aircraft to the same specification enable the production line to flow smoothly with a corresponding reduction in costs, and in order to achieve this objective for B.206 aircraft the production programme specifies two standards of build which anticipate minimum customer requirements. Differing standards of radio and navigational aids are required to suit home and export markets and by addition to the basic fits a wide range can be provided.
Advancement in Aeronautics
Authors: Baxter A.D.
Published: February 2008

THE history of the Society is a fascinating subject and one worthy of considerable study. On January 12, 1866, six men met at the London home of the eighth Duke of Argyll to found, the Aeronautical Society of Great Britain. They declared their belief in the achievement of human flight and their determination to advance it scientifically. Of the six founders, the three who contributed most to its advancement were James Glaisher, astronomer and meteorologist and a Fellow of the Royal Society, F. H. Wenham, a marine engineer, and F. W. Brearey, convenor of the first meeting, who was neither scientist nor engineer but an enthusiast who was to be the Honorary Secretary of the Society until 1896. These three played complementary parts, but it is probable that the contribution of Wenham exerted most practical influence on the Society's progress.
The Economics of Aircraft Noise Suppression
Authors: Greatrex F.B.
Published: February 2008

DISCUSSIONS on aircraft noise problems unfortunately result too often in inconclusive statements of good intentions on the one hand from those who are connected with making the noise, or emotional recrimination on the other from those who have to suffer it. Administrators and even eminent aircraft designers protest ignorance of acoustic technology, while sufferers from noise show a marked reluctance to face the most elementary economic facts. Perhaps one of the reasons why many people are still suspicious of technology in this country is that we have not yet mastered the art of presenting all the factors, and particularly the economic factors, in a technological problem in such a way as to make it possible to see clearly the issues involved. This paper is an attempt to give a better understanding of the interactions between the technical, economic and political sides of the aircraft noise problem. It is meant to show how these interactions might be studied, rather than to give definite answers to specific problems.
Developments at Electro‐Hydraulics
Authors: Phillips R.A.
Published: February 2008

RECENT developments at Electro‐Hydraulics Ltd. are in two categories: in component design and in solutions to basic hydraulic problems. Examples shown below are selected from a number of fairly recent component design details, followed by an outline of developments in seals and a summary of fatigue tests on hydraulic tubes.
A New Development in Multiplex Electro‐hydraulic Actuators
Authors: Maltby P.J.
Published: February 2008

THE continuing development of aircraft operational concepts has in recent years resulted in the emergence of a variety of flight control functions which are essential to the safety of the aircraft and which moreover have to be performed automatically, the task being either too difficult for the human pilot, or at least so difficult as to command so much of his attention that his ability to carry out other functions is impaired. Among these functions may be instanced automatic landing, autostabilisation of V.T.O.L. aircraft in the hovering flight mode, the autostabilisation of an aircraft in some part of the flight regime in which its own natural stability is negative, and the autopiloting of aircraft operating at extremely low relative altitudes, to avoid collision with the terrain.
Design, Operation and Support of the Boeing Supersonic Transport
Authors: Becker John W.
Published: February 2008

THE aviation industry is undertaking development of the most comprehensive support programme in its history—the support programme for the supersonic transport. Boeing's SST, for example, will cost over $35 million and will cruise at 30 miles a minute at altitudes of 60,000 ft. or more. The aircraft is being designed to achieve a dispatch reliability of 99 per cent, a design life of 50,000 hours, and a utilization potential of 3,000 hours per year to meet fully its economic objectives. The kind of support programme the SST will require can only be found by examining some of the aspects of this new aeroplane.
The B.A.C. One‐Eleven in America
Authors: Edwards S.J.
Published: February 2008

BY the end of 1966, no fewer than 57 B.A.C. One‐Eleven Series 200 and 400 airliners had been delivered to four airlines and two industrial organisations in the U.S.A. This is a remarkable achievement for the U.S. market is unquestionably far and away the most difficult for a European airliner to penetrate in depth.
The Olympus 593 Powerplant for Concorde
Authors: John Derek J.
Published: February 2008

SUMMARY THE optimum powerplant for a Mach 2.2 transport aircraft is a turbojet. The Olympus 593, latest of a well‐proven family of twin spool, axial flow turbojets has been designed especially for installation in the Concorde. Invaluable development has been achieved from two 90% scale engines and the first seven full size engines. Satisfactory fuel and oils are now available for Concorde and the powerplant has already flown in a Vulcan flying test bed.
An Accident and Maintenance Recording System
Authors: Hynes Jack
Published: February 2008

CIVIL Aviation authorities throughout the world have introduced, or are in the process of introducing, legislation which requires passenger‐carrying aircraft operators to install a flight data recording device. The recorder will monitor a number of parameters which, it is felt, would be an aid to accident investigation procedures; in addition it will have to survive the environmental conditions which would exist in the event of an aircraft crash. Regulations differ from country to country, but in general the American Federal Aviation Agency, the British Air Registration Board, and the Canadian Department of Transport set the standard.
Future Requirements of Adhesive Systems
Authors: Ris D.
Published: February 2008

ESTABLISHING A STANDARD SOME twenty‐two years ago Dr de Bruyne invented the Redux system for joining metal to metal in a manner suitable for use in aircraft construction The phenol‐formaldehyde/polyvinyl‐formal formulation of this system is still widely used today. What is it that has made this system such a success through the years?