bluuebunny/crossref_metadata_2025 huggingface dataset:
The Problem of Fatigue Strength in Aircraft Structures
Authors: Gassner Ing. E.
Published: February 2008

IN aircraft construction, until about fifteen years ago, the customary static method of stressing generally also provided for an adequate fatigue strength. This does not now apply for various reasons (e.g. increased flight speeds, use of high‐strength materials with changed fatigue properties). It is, therefore, necessary to establish design rules which take account of more recent knowledge; which variables are to be specially considered, and what their importance is in a particular case, becomes clear from fatigue tests which, to a considerable extent, cater for the peculiar loading conditions of flight (service endurance tests or programme‐loading tests). The principle of these tests was established in the DVL (1938 to 1941) and it is now in general use in automobile design for determining the relation between fatigue strength and endurance (life function) as in many cases of service failures a very good agreement with these tests can be observed.
The Library Shelf
Authors: E.G.B.  , A.R.F.
Published: February 2008

The subject of aeroelasticity is not well provided with text books and this makes the present book all the more valuable. One difficulty in writing such a text book is that although aeroelasticity is often regarded as a highly specialized subject and tends to be avoided by the average aeronautical engineer, yet it embraces a very wide field of study covering matters as diverse as linear aerofoil theory, both steady and unsteady, some boundary layer effects, structural theory for distortion of the aircraft components, problems of servo analysis and mathematical methods for the solution of large numbers of linear equations with real and complex coefficients. Thus, although the book contains nearly 500 pages it is correctly entitled ‘An Introduction …’ and the author presents each of his subjects with diversions into pure mathematics where necessary. These mathematical sections include introductions to Lagrange's equations, matrices and Laplace transformations.
Probe Measurements in Three‐Dimensional Flow
Authors: Winternitz F.A.L.
Published: February 2008

A survey is made of the instruments and methods used to measure total and static pressure and direction in three‐dimensional flow. Comparative tests in a towing tank of two designs of live‐orifice pitot‐type probe showed the advantage, within a limited range of flow inclination, of the instrument with independent static pressure orifices. Speed and angle of flow characteristics are Riven for these two probes, which differed in the shape of head.
Some New Materials for Missile and Power‐plant Applications
Authors: Levy A.V.
Published: February 2008

THE missile and power‐plant designers of today are continually in need of materials to withstand higher loads and higher operating temperatures. The development of the high‐speed guided missile is dependent on the output of the materials laboratory for new materials of superior properties and new methods of fabrication. The materials engineer has thus far been able to keep abreast of the demands for better materials. Several new materials, all developed for elevated temperature operation, are at present available in some state of experiment or production for consideration in the design of advanced performance missiles and power‐plants.
Strut Interference on an Aerofoil
Authors: Lockwood Taylor J.
Published: February 2008

IT is fairly standard practice to correct wind‐tunnel results for a model or aerofoil by taking measurements of lift, etc., with and without dummy supports fitted, the correction for support interference being deduced accordingly. Such experimental correction figures are liable to be rather scattered owing to various causes, and it is useful to have at least some independent check by direct calculation on the amount of interference to be expected.
The Optimum Design of Long‐Range Aircraft
Authors: Sanders Karl L.
Published: February 2008

IN the present paper an attempt has been made to determine the optimum aspect ratio, wing loading and fuel load ratio under certain specified design conditions. Aeroplanes with turbojet as well as with airscrew propulsion have been considered.
Helicopter Longitudinal Stability
Authors: Payne P.R.
Published: February 2008

A NUMBER of approaches to the calculation of rotor downwash have already been discussed. Broadly spsaking, the methods of Castles and DeLeeuw and Squire and Mangler are the same. In both methods the downwash at the rotor disk is assumed to be perpetrated in a helical downwash sheet which, as the slipstream, extends below the rotor to infinity. The downwash in the disk due to the bound vortices, and the additional downwash in the disk which is induced by the helical sheets in the slipstream (Castles and DeLeeuw substitute downwash rings for helices, in the interest of mathematical simplicity) is calculated, on the assumption of an infinite number of lightly loaded blades. The final results of Castles and DeLeeuw on the one hand, and Squire and Mangier on the other, are in very wide disagresment. This disagreement is principally due to the fact that, whereas the first investigation assumes constant circulation along the blade (ideal twist and taper), Mangier and Squire assume a ‘practical’ variation of the form likely to be encountered on an untwisted untapered blade. We conclude that the radial distribution of lift on a helicopter blade will have a profound effect on the downwash pattern: which in turn will affect the calculated lift.
Factorizing Polynomials
Authors: Head J.W.
Published: February 2008

IN a recent paper1 the author suggested that Lin's reduced penultimate remainder process could still be used to find the real or complex linear factors of polynomials of any degree, even when the process originally described by Lin2 was divergent, provided that the initial approximation to the linear factor being sought, and the two succeeding iterates, could be regarded as differing from the root sought by a small quantity of the first order. The main principle used was that in this linear case the convergence or divergence of the successive iterates to or from the root being sought was purely geometric, so that (for a sufficiently close starting approximation) the root being sought could be deduced from two iterations; complex numbers, however, might be involved in the iteration process.
Eighth International Astronautical Congress
Authors: Thompson G.V.E.
Published: February 2008

Data on the behaviour of materials at high temperatures are needed to improve current designs for missile skins, rocket motors, gas turbines and nuclear applications, but it is only within the last few years that new research tools have been developed to enable materials to bs studied under such conditions in the laboratory. This paper reviews the available techniques, with emphasis placed on the range 2,000–5,000 deg. K.: furnaces (electric resistance, induction, arc, solar), high‐intensity electric arcs, flames, combustion of molten metals, shock tubes, ultra‐high‐frequency are discharges, plasma jets, thermonuclear reactions.
Ground Performance at Take‐off and Landing
Authors: Kettle D.J.
Published: February 2008

A simple chart is presented for the rapid evaluation of either unstick or landing roll distance. The method is incomplete in that it docs not deal with the airborne phase of take‐off and landing manoeuvres; it is necessary to estimate this part separately. The chart is strictly applicable only when wing incidence remains constant for the whole of the ground run. In the case of the landing roll, some uncertainty exists as to the precise value of µ, the braking coefficient of friction. An attempt is made to relate an equivalent value of µ to touchdown speed for the standard wet and dry runway as adopted by I.C.A.O. assuming that automatic brakes are fitted, with a maximum braking force equal to 0.35 of the landing weight.
Pneumatic Jet Nozzle Control
Authors: Stephenson J.M.
Published: February 2008

THE principal reason for fitting a variable throat area nozzle to a turbojet engine, instead of a simple, fixed pipe, is to permit afterburning (fig. 1), whereby the temperature of the propelling gas may be more than doubled. The throat area of the nozzle must be increased approximately in proportion to the square root of the temperature, so that the jet pipe pressure is not much changed. Otherwise, the pressure rises sharply when the afterburner is lit, and throttles the compressor: the drop in airflow may then cause the engine to overheat and surge. The aim of a nozzle control system is thus to keep the rotating components unaware of whether the afterburner is alight or not, and safe from damage due to pressure and temperature transients.
Jet Drag of Wings with Jet Flaps
Authors: Payne P.R.
Published: February 2008

AN analysis of the mechanism of jet drag is given by Stratford, it being suggested that jet drag is zero if the density velocity products of the free‐stream and jet are equal, among other conditions. Under certain conditions Stratford concludes that ‘negative’ jet drag (i.e. thrust augmentation) is possible.
Some Effects of Kinetic Heating on the Stiffness of Thin Wings‐II
Authors: Kochanski S.L. , Argyris J.H.
Published: February 2008

The Third Power Approximation introduced in the previous section is here applied to determine the stiffness characteristics of symmetrical double‐wedge wings subjected to large flexural and torsional deformations. This method is believed to yield results of sufficient accuracy for practical purposes, even for wings with a thickness/chord ratio as low as 3 per cent, as long as the spanwise curvature and the maximum stresses are in the range of engineering applications. As mentioned in the Introduction it is also possible to derive an exact solution in terms of Bessel functions but its complexity limits its practical interest.
Rotary Wing Papers at the I.A.S. Annual Meeting
Authors: Payne P.R.
Published: February 2008

THE twenty‐sixth annual meeting of the Institute of Aeronautical Sciences was held, as usual, in the Sheraton‐Astor Hotel, New York. The papers delivered during the week covered the widest range of subjects to date, including gravity, and anti‐gravity, hypersonic aerodynamics, space propulsion and earth satellites, to name only an exotic few. It is obvious that any one observer can give a coherent summary of (or even attend) only a limited number of lectures, and this report is concerned only with the rotary wing sessions.
Experimental Data on Turbulent Wall Jets
Authors: Sigalla A.
Published: February 2008

IN a recent article on the protection of refractories in steel‐making furnaces, Chesters et al. discussed the application to furnace design of jets blown over surfaces. The theory of the wall jet is given by Glauert, who mentions as typical examples the flow produced on the ground by the downward directed jet of a vertical take‐off aircraft, and the flow produced under certain circumstances in canal sections separated by a sluice. Jacob et al. and also Zerbe and Selna have reported experiments on wall jets which were carried out as background work to the general problems of ice and fog formation on the inside surface of aircraft windshields. Other experiments have been carried out by Förthmann and also by Sigalla and Painz in the Fluid Dynamics Section of the British Iron and Steel Research Association, Physics Department.
Higher Harmonic Rotor Control
Authors: Payne P.R.
Published: February 2008

The elimination of the retreating blade stall speed limitation for helicopters by means of an appropriately programmed feathering input is studied for the general case of a rigid flapping blade with hinge constraint (thus making the results applicable to conventional, offset‐hinged or cantilevered rotor blades). It is concluded that second harmonic feathering alone will not be particularly effective in delaying the stall limit, but that a suitable programme of several higher harmonic inputs will enable the retreating blade stall limit to be pushed beyond the advancing blade compressibility limit. In the course of the investigation generalized equations were developed for blade flapping to the nth harmonic under the influence of feathering to the nth harmonic. The resultant matrix is symmetrical and checks with the few available limit cases derived by other workers. Because of loose coupling in the matrix generalized equations can be derived giving the effect of any particular harmonic of feathering upon flapping and angle of attack distribution around the disk. The effect of higher harmonic feathering upon rotor stability derivatives is not discussed in this text, but examination of the equations indicates that an improvement in stability could be obtained by the application of second harmonic control. This paper does not discuss the mechanical details of obtaining a higher harmonic feathering input, nor is it suggested that this is necessarily the best means of obtaining higher forward speeds. In certain cases it may be the only means however.
Third A.G.A.R.D. Combustion and Propulsion Colloquium
Authors: Lefebvre A.H.
Published: February 2008

THE Combustion and Propulsion Panel of A.G.A.R.D. (Advisory Group on Aeronautical Research and Development to N.A.T.O.) held its third Colloquium at Palermo, Sicily, during the period March 17–21, 1958. Nearly 200 delegates attended the Colloquium representing 10 different N.A.T.O. countries. There were 19 delegates from the U.K. and 12 of these participated either as authors, reviewers of papers or to the discussion. During the five‐day period, 18 invited papers were presented with prepared comments from 45 selected reviewers.
Ultrasonic Resonance Testing adhesives of Glued Metal Joints
Authors: Schijve J.
Published: February 2008

NON‐DESTRUCTIVE testing of glued metal joints for voids in the glue line may be done by vibration tests. The response to an excitation will be different for adhesive joints with and without voids. The difference in response will depend on the frequency of the excitation. This may be chosen in the sonic as well as the ultrasonic range. Each will have its own merits.
The Recovery of an Aeroplane from a High Speed Dive
Authors: Young A.D. , Neumark S.
Published: February 2008

Detailed step by step calculations have been made of the recovery with fixed elevator from a high speed dive for three different aircraft; for these calculations measured wind tunnel data were used. The aircraft differed markedly in the behaviour of their restoring margin Km=− (∂Cm/∂CL)M. The calculations demonstrated in all cases an initial, rapidly damped, short period oscillatory phase, a nearly constant value of ρV2 throughout the recovery, and subsequent to the initial oscillatory phase Cm was small. These results enable three different approximate methods for calculating the recovery after the initial oscillatory phase to be developed. The first is applicable where only a rough estimate of the recovery characteristics is required and the value of Km is about 0·3 or greater; it is very simple and quick to apply. The second is only a little more complicated and is found to give reliable results where Km is of the order of 0·1 or greater. The third method is the most complicated of the three but is still fairly simple and quick and it can be expected to give reliable results in all cases except where Km is appreciably negative for a considerable portion of the recovery. In the latter case, however, the aircraft is liable to be unstable and detailed step by step calculations or simulator studies are essential for an accurate assessment of the recovery. The main features of the initial oscillatory phase are satisfactorily predicted by Gates' manoeuvrability theory if the restoring margin Km is adequately positive (that is, greater than about 0·005) and if this factor docs not vary rapidly with Mach number at that stage. No detailed investigation has been made for aircraft diving at supersonic speeds; however, it seems likely that the general results of this investigation will still apply in such cases.
Ultrasonic Testing of Compressor and Turbine Blades for Fatigue Cracks
Authors: Schijve J.
Published: February 2008

Special probes were developed to test rotor blades for fatigue cracks. These probes utilize ultrasonic surface waves which are highly sensitive to fatigue cracks. The dimensions of the probes were kept small to make possible the testing of blades without the necessity of dismounting. The probes are built up from conventional commercial probes by attaching some small auxiliary equipment to them, which is very easy to manufacture. Searching blades with these probes is more reliable and less time‐consuming than with previously available methods.
Simple Models for Aeroelastic Demonstrations
Authors: Boyd E.A. , Johns D.J.
Published: February 2008

Many colleges wish to demonstrate aeroelastic phenomena and require only qualitative answers. For this purpose the more easily constructed the model the better.
Photographic Pyrometry of Rocket Exhaust Jets
Authors: Simmons Frederick S. , DeBell Arthur G.
Published: February 2008

A photographic technique for determining temperatures in luminous rocket exhaust gases is reviewed, and some recent refinements in the reduction and analysis of the film records are described in detail. Some values of temperatures measured at the nozzle exit of a small rocket motor are compared with theoretical values based on measurements of the pressure in the chamber, the propellent mixture ratio, and the dimensions of the motor. The use of the method in studies of the expansion process in rocket nozzles is discussed.
A Theoretical Approach to the Conversion Stage of Tilting Rotor Convertiplanes
Authors: Sutherby P.F.
Published: February 2008

RECENT developments in the field of convertible aircraft have shown the practicability of numerous methods of achieving vertical take‐off, combined with forward flight that is largely, or completely, supported by fixed wings. The aerodynamics of aircraft which derive their hovering lift from jet thrust are straightforward since there is no down‐wash to complicate the airflow over the wings; if a rotor is used, however, the wash of the rotor will vary from a relatively minor effect in forward flight to the only source of airflow over the wings in hovering.
The Analysis of Fuselages of Arbitrary Cross‐section and Taper
Authors: Argyris J.H. , Kelsey S.
Published: February 2008

Following the self‐equilibrating stress systems developed for the single‐cell fuselage, further stress systems are given for the fuselage with a double‐cell cross‐section. These allow for the direct stress carrying ability of the floor. Wing‐fuselage interaction redundancies are discussed in detail and suitable self‐equilibrating load systems presented. The formation of the associated stress systems in the cover is described with reference to their generation inside the computer. Chapter IV concludes with a brief account of fin attachment loads which serves to introduce two further interaction redundancies to take account of skin attachment. The opening section of Chapter V relates the detailed frame loads to the overall fuselage loading preparatory to the analysis of the closed frames. Matrix equations for the calculation of the statically equivalent wing reactions and of the fuselage moment diagrams are given.
Anti‐Vibration Mounting of Aircraft Power Plants
Authors: Harriman J.F.
Published: February 2008

Early aircraft engines were usually bolted direct to the aircraft structure and no attempt was made to prevent the vibrations which they set up from being transmitted to the airframe. With increasing engine powers and the use of larger airscrews these vibrations eventually become of sufficient magnitude in some cases to cause annoyance to the occupants of the aircraft and also failure by fatigue of parts of the structure. Various attempts were made both to analyse the source of the vibrations with a view to eliminating them or reducing them to an acceptable magnitude. Where this was not possible attempts were made to isolate the disturbances from the airframe and its occupants. This paper presents the basic theory of vibration isolation and gives an account of the various sources of vibration met with in reciprocating, turbo‐propeller and pure‐jet installations. The loads acting on the engine during various conditions of flight are then examined as a knowledge of these is required in order to determine the strength of the supporting units. Various practical engine mounting configurations are then considered which will give vibration isolation together with adequate support of the engine under all conditions of flight. Some account is given of the properties of rubber and the design and testing of rubber vibration isolators, and some installation problems are examined. Finally, the complete programme of testing an installation both on the test‐bed and inflight to evaluate the degree of vibration isolation achieved is described, together with various criteria of acceptability both from a structural and physiological standpoint. A bibliography covering the various sections is included.
The Analysis of Fuselages of Arbitrary Cross‐section and Taper
Authors: Argyris J.H. , Kelsey S.
Published: February 2008

Continuing Chapter V, internal stress resultants are established for the open rings in (he fuselage due to the various statically equivalent and self‐equilibrating load systems. The determination of the frame redundancies leads immediately to the corresponding results for the closed rings. The procedure is developed for both single‐ and double‐cell cross‐sections with cither singly‐or doubly‐connected rings. A brief account is also given of the flexibility of a diaphragm or bulkhead, describing how cither the force or displacement method may be used. The analysis of the fuselage basic system concludes with an investigation of thermal stresses in the closed frames.
The Library Shelf
Authors: B.S.O.  , DE J.C.
Published: February 2008

The first number of the sixteenth volume in this series contains eighteen papers covering the usual wide range of topics. The longest paper describes a photoelastic investigation carried out in the U.S. Naval Research Laboratory, Washington, D.C., to determine the dynamic stress distribution surrounding a running crack. Iso‐chromatics were obtained using the Schardin multiple spark technique, with the optical system modified for the method of fringe multiplication. Principal stress distributions were found by means of an optical interferometer with single spark illumination, using a number of similar models. Principal stresses were corrected to allow for the variation of stress‐optical sensitivity with time. It was found that the dynamic distribution approximates to that in a statically loaded specimen extended at its ends by a fixed displacement. The zone of stress disturbance grows in all directions proportionally to crack length. The average stress on the remaining uncracked cross section increases with length of crack to a maximum of about 1½ times the original value. Measured terminal crack velocities agreed well with calculated values. The discussion compares the results with theoretical analysis.
The Analysis of Fuselages of Arbitrary Cross‐section and Taper
Authors: Argyris J.H. , Kelsey S.
Published: February 2008

The analysis of the wing/fuselage and fuselage/tail unit interaction forces is extended to cover the case when the attached component is more conveniently analysed by the Matrix Displacement Method. The flexibility matrix of the complete aircraft, supported on the wing/fuselage attachment points, follows from the results derived in this and previous sections and takes into account the elastic interaction between the various components. The dynamical matrix of the complete free aircraft is set up and for completeness the theory and properties of the normal modes of vibration are given. A final sub‐section discusses some points of detail in the mass distribution and the definition of the forces on the aircraft.
The Library Shelf
Authors: H.L.P.  , F.B.
Published: February 2008

According to the preface to this book, the intention of the author is to present a reliable account of the latest theoretical developments in those fields of dynamics and aerodynamics directly associated with the work of helicopter project design. At the same time it is regarded as essential that the closest correlation be maintained between theoretical and practical results. These are admirable objectives in themselves, and nobody would dispute the value of such a book were these objectives fulfilled. The most truthful thing that can be said of Helicopter Dynamics and Aerodynamics is that an almost bewildering range of relevant topics is discussed, and that a few distinctive and novel features are discussed at greater length than anywhere else. Unfortunately the book is so full of misprints and mathematical errors that the reader is left in considerable doubt as to what can reliably be accepted, and in no doubt at all about some results which are demonstrably false. This is a pity, as certain aspects of the work may well be of far reaching importance, but their acceptance as they stand without further extensive investigation calls for a considerable act of faith.
Blown Flaps for Stol Operation
Authors: Schwartzberg Milton A.
Published: February 2008

There has been some speculation anions STOL aircraft designers (hat a net increase in lift might be realized from a combination of blown flap and slip‐stream deflexion. A recent wind tunnel investigation confirms the speculation for large flap deflexions. At small flap deflexions, however, the lift gained by the combination is less than the sum of the separate contributions. The effect at medium flap deflexion is dependent on the strength of the slipstream. These results should be applicable to most configurations with a blown plain flap in the slipstream behind the propellers.
Nomogram Analysis for Ducted Fans with Pre‐rotation
Authors: Gibson M.M. , Norbury J.F.
Published: February 2008

IN order to determine the performance of a ducted fan over a range of off‐design operating conditions it is possible to use the nomogram method of analysis described by J. F. M. Scholes. The method requires the use of a number of charts, each one being applicable only to a single radius ratio. Moreover each chart depends on the aerofoil characteristics of the blade element, so that it applies only to a single section shape operating at a given Reynolds Number. No account is taken of interference effects or compressibility. Despite these limitations the nomogram method may be valuable if it is required to analyse a number of fans employing the same blade section over a similar range of Reynolds Numbers.
The Library Shelf
Authors: A.D.Y.  , B.W.M.
Published: February 2008

The term ‘hypersonic flow’ was first used by Tsien in 1946 to denote a (low for which the main stream Mach number was large compared with unity, and he demonstrated that such flows displayed characteristic features which justified the use of a special name. Tsien confined his considerations to a perfect gas with constant specific heats but since 1946 interest has widened to the flow of real fluids at high Mach numbers, this interest being mainly stimulated by the problems of the re‐entry at high speeds into the earth's atmosphere of missiles and satellites. An essential feature of hypersonic flow is that relative to the undisturbed flow direction the inclination of the nose shock of a body immersed in the fluid is of the same order of magnitude as the mean inclination of the surface over the forward part of the body, and the region between shock and body, the so‐called ‘shock layer’, is relatively narrow there. Another characteristic feature is the high temperature that developes in this layer in problems of practical interest and the associated effects on the physical and chemical properties of the medium. Thus, not only must account be taken of the variation of the specific heats with temperature for a real fluid but the consequences of dissociation and ionization of the fluid on crossing the nose shock must be considered. The interaction of the boundary layer with the flow external to it and with the nose shock becomes of increasing importance, as well as increasingly complex, with increase of main stream Mach number. Finally, account must be taken of the molecular nature of the medium in problems where the density is sufficiently low for the mean free path of the molecules to be a significant ratio of a typical dimension of the body or of its boundary layer thickness.
Ground‐Effect Machines
Authors: Boehler G.D.
Published: February 2008

An analysis is made or the basic principles which govern the operation of those air‐cushion devices otherwise known as ground‐effect machines (GEMs). Most of these vehicles can be defined as machines which operate in close proximity to the earth's surface without ever physically touching it because they are always separated from it by a cushion or a layer of air, however thin; as a consequence, propulsion and control of GEMs must be of an aerodynamic nature. The only machines not covered by this definition are special types of over‐water GEMs. It is proposed to establish six main categories of GEMs from which all other possible configurations could be evolved by proper combination of the basic types. For each of these six configurations, a critical biographical survey is made and some comparative features are pointed out. The overall picture is one of great complexity because of the large number of parameters involved. This points out the danger of a ‘hardware’ approach to the GEM problem until a firm base of comprehensive research has been established. At the present time, the emphasis placed on the annular jet seems justified, inasmuch as the annular jet represents a good compromise between versatility, simplicity and performance.
Topological Aspects of Structural Linear Analysis
Authors: de C. Henderson J.C.
Published: February 2008

The selection of a system of cut releases which would render a continuous skeletal structure statically determinate is governed principally by the topological and geometric characteristics of the structure, and to a lesser extent by its material properties. Only the topological aspects will be considered here, the other factors being purposely excluded. It is shown how the knowledge of the topology of the structure can be exploited to improve the conditioning of the associated equations of compatability. Owing to difficulties inherent in the design of any automatic procedure for the reduction to a canonical form, a method of condensation has been evolved for complex multi‐member structures. In this way the large scale features of the structure are taken into account without neglecting the effect of local characteristics.
The Library Shelf
Authors: H.L.P.  , J.C.
Published: February 2008

The publication in English of Gantmacher's book ‘The Theory of Matrices’ is of particular interest in that it reveals to us the standard attained by a Russian textbook in that particular field. If this book is typical of the standard of other Russian mathematical works, the translation of many more of them would be something to be warmly welcomed. The translator, Professor K. A. Hirsch, is himself an outstanding authority on matrix theory, and the fact that he has undertaken the translation is in itself a compliment to the original book. It takes only a little reading to reveal that the translation has been performed with felicity and that the style is all that can be desired.
Modern Trends in the Manipulation of Metals
Authors: Keil C.G.
Published: February 2008

THE paper began with a brief historical survey of the cold extrusion process since its first practical use over sixty years ago. The extrusion of special materials such as molybdenum, beryllium and zirconium was described. The problems relating to the production of suitable tooling for the extrusion process and the preparation, heat treatment and lubrication of extrusion billets and slugs were discussed. Following discussion on temperature and speed effects, prestrain of work material, presses for extrusion and component design, the paper concluded with an outline of the applications and advantages of the cold extrusion process.
New Plant for Rolling Aluminium
Authors: Keil C.G.
Published: February 2008

IT was in September, 1950, that Alcan Industries Ltd. (or the Northern Aluminium Co. as it then was) opened the continuous strip mill at Rogerstone in South Wales. In March, 1958, new plate handling facilities were inaugurated, and it was announced at that time that the company had embarked on a four‐year programme of expansion which would involve an investment of a further £8 million in new plant and buildings, with the intention of increasing the output of rolled aluminium to 75,000 tons a year. This ambitious programme has now reached the halfway stage with the installation of a 144 in. hot rolling mill, and on October 6 Alcan Industries Ltd. invited us to inspect the present stage of development at the Rogerstone works.
Supersonic Wind Tunnels
Authors: Keil C.G.
Published: February 2008

ON October 19 the Minister of Aviation formally opened the two new high‐speed wind tunnels which have been constructed at Wharton, Lancashire, for English Electric Aviation Ltd.
The Analysis of Fuselages of Arbitrary Cross‐section and Taper
Authors: Argyris J.H. , Kelsey S.
Published: February 2008

The conditioning of the redundancy equations is discussed and a method is given for drastically reducing any serious coupling between primary redundancies originating at the same ring station. Making use of the latent root programme of the computer, a revised transformation matrix, for the definition of the primary redundancies, is developed for the specific cross‐sectional shape and geometry when this is markedly non‐circular. The method is illustrated by application to a number of sample cases. Coupling between redundancies at different ring stations is also discussed, but is not considered to be serious except with unusual patterns of frame flexibility.
Pressure Forces on Variable Conical Nozzles
Authors: Woods W.A.
Published: February 2008

REHEAT systems for turbo‐jet engines employ variable area convergent nozzles, and modern developments have produced nozzles made up of a series of flaps or fingers, as shown in fig. 1. These flaps have to be supported against the internal gas load to maintain a given area. The turning moment on each flap is usually balanced by a single element through a mechanical linkage; the element may take the form of a rod in tension or a shaft in torsion. This note provides a theoretical study of the nature of this load. In addition, the concept of frictional forces is introduced and a method developed for calculating the forces prevailing in flight, provided that two constants are determined from sea level test results.
Turbine Powered Transport Aircraft in the U.S.S.R.
Authors: Ritchie D.J.
Published: February 2008

THIS paper is not intended to provide any startling revelations of Soviet technology but is a detailed survey and analysis of contemporary developments in Soviet turbine powered transport aircraft. The major portion of the work is based on Soviet sources of information in an attempt to assure authenticity and accuracy.
Transient Temperature Distributions in an Insulated Multi‐Spar Wing
Authors: Capey E.C.
Published: February 2008

An approximate method is employed to derive the transient temperature distributions and thermal stresses in an idealized insulated multi‐spar wing subjected to aerodynamic heating. Approximate formulae obtained by this method arc compared with exact solutions for a number of special cases, and are found to be in good agreement.
Topographical Navigation Display
Authors: Honick K.R.
Published: February 2008

FLIGHT experience during recent years with roller strip maps driven from Doppler groundspeed data in an ‘along’ and ‘across’ track mode has demonstrated many of the undoubted advantages of a pictorial display of ground position.
Design Considerations of Russian Air‐to‐Air Guided Missiles
Authors: Ritchie D.J.
Published: February 2008

PHOTOGRAPHIC details of various aircraft and missiles recently released in conjunction with the Soviet air show at Tushino Airport on July 9, 1961, has provided a basis for the start of an evaluation of Soviet air‐to‐air rocket weapons. These pictorial data, coupled with Russian textbooks, as well as evidence of Soviet interest in the guided‐missile work of the Western Powers, indicated by the material that has been translated from English into Russian,1 has led to this brief evaluation of their work in this field.
Predicting the Performance of Jet Flap Configurations
Authors: Pivko S.
Published: February 2008

A simplified method for estimating the aerodynamic properties of thin flapped aerofoils influenced by high velocity jet sheets is developed. It is assumed that the main flow around the aerofoil does not influence the velocity distribution in the jet. Considering also the effect of the mixing with the surrounding air, a real jet is supposed to be replaced by an appropriate aerodynamic model, having a linear downstream distribution of velocity adopted on the basis of test data. Both thin aerofoil and the jet sheet are adequately replaced by vortex distributions,so that the lift and the pitching moment of the aerofoil influenced by the jet may be evaluated in the usual manner. Comparison with some available experimental results shows that the proposed semi‐empirical method gives good agreement with experiment.
The Static Hole Error Problem
Authors: Livesey J.L. , Jackson J.D. , Southern C.J.
Published: February 2008

Experiments have been carried out to determine the magnitude of static hole errors for holes of various diameters and depths. A new approach is tried to the problem of extrapolation to zero hole size for the purpose of obtaining a true value of static pressure. The results obtained are in broad agreement with previous experimental data and confirm the fact that a positive error is obtained for deep static holes, whereas shallow holes with large cavities behind them can involve negative errors. Since the effects of hole size and hole depth are apparently opposite, the use of fairly shallow holes can result in pressure measurements which are very close to the true value, provided that in drilling the holes no distortion of the duct wall is produced and all burrs are carefully removed. This point may be of interest in some engineering applications where the material used in the construction of the duct or model is thin.
Natural Vibrations of a Free Structure
Authors: Jennings A.
Published: February 2008

THE matrix flexibility method for the prediction of the normal modes of vibration of a structure may be extended to the case of a structure which has no external supports. This is of particular relevance to problems of aircraft and missile vibration.
Optimum Power Plant Configuration for a Supersonic V/S.T.O.L Strike Aircraft
Authors: Denning R.M.
Published: February 2008

Examples of jet‐lift aircraft powered by the diverse systems of the single lift/thrust turbofan and the multi‐engined specialized lifting and propulsion engines are now flying. With the experience gained from these pioneering aircraft, it is appropriate to review the thermodynamic characteristics required of engines for future ‘vectored thrust’ low‐level strike aircraft, having supersonic capability. The relative merits of extreme forms of power plant are discussed from the engine and power plant designer's viewpoint and these are linked with a spectrum of aircraft which lie between these extremes of design.
Transient Vibrations of Missiles and Space Vehicles
Authors: Benfield W.A. , Cox H.L. , Chan S.P.
Published: February 2008

A method of analysis for determining the transient forced flexural vibrations of accelerating missiles and space vehicles is presented. The equations of motion are in matric form and may be readily adapted to electronic digital computers. The matric formulation for the problem is written to include the effects of engine gimballing resulting from structural coupling of the flight control system, inertial axial loads along the missile, variable stiffness, variable mass, variable mass moment of inertia, variable shear stiffness, structural damping, structurally coupled aerodynamic forces and arbitrary transient forces applied along the missile. Only the basic data for the system are required in the matrices.
Tooling for the Industry
Authors: Branston J.L.
Published: February 2008

PLASTICS tooling has been accepted progressively in the aircraft industry, particularly during the past decade, mainly because of its elementary manufacturing equipment requirements and the saving it provides in time and labour. However, its continued success depends on knowledge of the properties of these materials and skill in applying them. Although metals are the traditional materials for machining or fabricating tools, it is now being realized more than ever before that certain advantages can be gained by the use of plastics in tooling, particularly when considered in the light of job or batch production—these being most significant in the aircraft field—and resulting in improved efficiency and economics. It must, however, also be appreciated that these materials have certain limitations, for in the past they have been adopted by tool designers all to readily as direct alternatives to conventional materials for reasons which were not always well founded.
Aviation Fuel Problems
Authors: Goodger E.M.
Published: February 2008

Flight, even under the most routine conditions, sets high standards of quality for all materials employed. Specifications for aviation fuels have never been obtainable without careful compromise between conflicting requirements, and present developments towards flight at higher altitudes and higher speeds accentuate existing problems and reveal new ones. This article attempts to review the known major problems arising with aviation fuels under these conditions of severity, and to indicate a number of practicable solutions.
Power Plant System for V/S.T.O.L Aircraft
Authors: Lombard A.A. , Heyworth A.J.
Published: February 2008

THE Society of Automotive Engineers' paper, upon which this article is based, followed very closely along the lines of an article entitled ‘Composite Power Plant System for V/S.T.O.L. Aircraft’ published in the December, 1962, issue of AIRCRAFT ENGINEERING [see Ref. (4)]—although the latter paper concentrated upon a description of the RB. 162 and the use of lightweight lift engines for a V/S.T.O.L. low‐level strike fighter. The S.A.E. paper has therefore been slightly condensed here, to avoid unnecessary duplication and a number of illustrations have been omitted. Throughout this paper there are references to the advantages of a multi‐engined aircraft for the V/S.T.O.L. fighter application in preference to the single‐engined type. These passages must be read in the light of the recent statement to the effect that Rolls‐Royce have submitted to the Ministry of Aviation design proposals for a version of the Hawker PA 154 V.T.O.L. aircraft powered by two lift/thrust engines based upon the Spey by‐pass engine. These two lift (thrust engines would replace the single Bristol Siddeley BS.100 vectored thrust engine which is believed to have a thrust (with plenum chamber burning) of about 30,000 lb. Apart from the more obvious advantage of having two engines, i.e. safety, and the ability of the aircraft to complete the mission as a conventional aircraft if one engine fails, there is also the additional and attractive proposition that the Rolls‐Royce Spey engine is already in quantity production for a number of civil and military aircraft and could presumably be readily adapted to a lift/thrust configuration with front nozzle incorporating plenum chamber burning and rear nozzle. Finally, the reader is recommended to study in full the articles referred to in Refs. (2), (3), (4) and (5), in addition to this paper, since these provide a comprehensive survey of the jet lift field and in particular the application of jet lift to V/S.T.O.L. fighters. The six references listed on this page did not, of course, form part of the original S.A.E. paper—Editor.
A New Approach to Fatigue Testing
Authors: Knights R.N.
Published: February 2008

DURING the immediate post‐war years various techniques were adopted to improve the static strength of light alloys. Aircraft designers were quick to take advantage of these increased values with the result that stress levels generally were raised. Unfortunately the fatigue strength of the material was not improved at the same rate and a series of structural failures in the air dictated urgent investigation. At a later stage a similar situation arose during the strength development of steels.
Aeronautical Engineering at the University of Manchester
Authors: Hall I.M.
Published: February 2008

THE development of undergraduate teaching in Aeronautical Engineering at Manchester University has followed a different pattern from that in most other Universities in this country. Although Osborne Reynolds carried out his famous experiments in the Engineering Department at Manchester, the teaching of Aeronautical Engineering grew out of Mathematics rather than out of Engineering. For a large proportion of the past 80 years the Chair of Applied Mathematics has been held by men eminent in the field of Fluid Mechanics: Lamb, Goldstein and Lighthill must surely be names well‐known to every aeronautical engineer. It was due to the initiative of Professor S. Goldstein that a separate Department of Fluid Mechanics was set up in 1946 under the direction of Mr W. A. Mair. At first it was natural that the emphasis should be on experimental work to complement the theoretical work carried out in the Mathematics Department. Later, however, although close relations with the Mathematics Department were still maintained, the Mechanics of Fluids Department developed into a separate entity making both theoretical and experimental contributions to fundamental knowledge.
Brazed Pipe Joints
Authors: Duckworth D.J.
Published: February 2008

A METHOD of joining pipes which does not make use of heavy bulky fittings has always been required in the aircraft industry. In addition, as aircraft speeds increase well into the supersonic range, the need for more reliable joints that will withstand even more rigorous working conditions becomes apparent.
Wire Winding for Low Weight
Authors: Petts W.R.
Published: February 2008

WINDING high tensile steel wire on cylinders, or pressure vessels to increase their strength and resistance to internal stresses, is not a new principle. The Royal Ordnance Factories strengthened gun barrels in this way during the 1914–18 war, and in the years since the Royal Aircraft Establishment, Farnborough, has experimented with pressure vessels (fig. 1). The application of two layers of wire is intended to give a ‘fail safe’ condition to damp down the effects of a burst cylinder.
Preparation of an Overhaul Schedule for Use After a Heavy Landing
Authors: Decomps  , Caumont De
Published: February 2008

THERE seems to be little point in describing the ’product' which is the subject of this thesis since the Sud‐Aviation S.E.210 Caravelle twin‐jet, medium‐range aircraft is known the world over.
Design Considerations of the Russian Inter‐Continental Ballistic Missile and its Associated Space Booster
Authors: Ritchie D.J.
Published: February 2008

An Assessment of the Basic Design and Performance Based on a Heavily Retouched Photograph of a Large Ballistic Missile which was published in the December 4, 1962, edition of Kransnaya Zvezda (‘Red Star’). FOR the first time in any open literature source, the December 4, 1962, edition of Kransnaya Zvezda or Red Star, the daily newspaper of the Soviet Department of Defence, carried a very heavily retouched photograph of a very large ballistic missile with a caption describing the missile as their strategic rocket ready for launch. This photograph of a large rocket had obviously been heavily retouched so that little of its detail construction was identifiable. The rocket itself appears to have been cut out and pasted on to a photograph of a winter scene (fig. 1).