bluuebunny/crossref_metadata_2025 huggingface dataset:
Standardization of Aero‐Engine Components
Authors: Carvelli G.
Published: February 2008

STANDARDIZATION of engine components should start in the drawing office. To ensure uniformity in regard to method of dimensioning and standardization of data and notes, a system of sample drawing may be used. For example, if a drawing is to be made of a connecting rod, crankshaft, piston, piston ring, and so on, the draughtsman should refer to a list showing the sample drawing number for each particular part. The drawing may be obtained from file and used as a guide in producing the drawing. Fig. 1 shows one of these lists. To guide the draughtsman in selecting the proper sample drawing, a remarks column is used with a description oi the part.
Aircraft Structural Research
Authors: Shanley F.R.
Published: February 2008

IN so far as it is possible under wartime restrictions, the purpose of this paper is to present a comprehensive picture of the more important problems in aircraft structural design and research in the interest of advancing the knowledge of those engaged in industries which formerly had but slight connexion with aeronautical engineering, but today are deeply involved in various phases of aircraft work. A similar objective was stated by Dr. A. G. Pugsley as follows:
Design and Production Technique
Authors: Schroeder A.J.
Published: February 2008

FOR many years, a great deal of effort has been directed towards the possibility of reducing the cost of industrial production by means of special arrangements in the workshops. In this connexion outstanding results have been achieved on the basis of scientific management. Not until much more recently have corresponding efforts been extended to the subject of design, by taking into account trends of thought relating to economical production.
Sheet‐Metal Forming and Assembling
Authors: Schroeder William , Hazlett Thomas H.
Published: February 2008

THE modern aeroplane is constructed largely from sheet metal. As such, the most important production problems are those of sheet metal forming, and assembling. Production is here considered as not only the act of forming and assembling the required number of parts, but also the making of forming tools, and all processing of parts such as heat‐treating. Only that phase of the above concept of production which deals with the tooling for production and the forming and heat‐treating will be considered here. The design of the aircraft parts will also be discussed somewhat, for it is obvious that the design of the part (designed shape and materials used) frequently determines whether the part can or cannot be readily made.
Research for Aeronautics
Authors: Farren W.S.
Published: February 2008

THE invitation of your Council to deliver the Wright Brothers Lecture in commemoration, on this occasion, of forty years' development in aviation is an honour of which I am deeply sensible. The responsibility of doing justice to it would be heavy at any time. The turn of the tide of our joint fortunes in this War makes it greater rather than less. For the burden of success, whether in war or in peace, is far greater than that of failure. But so also is the stimulus to our courage.
A New Flexible Bearing
Authors: Burger F.E.
Published: February 2008

THE bearing described in this article may help to solve many problems peculiar to aircraft design, where deflections of large orders are experienced between one location and another.
Indium in Aviation
Authors: Murray William S.
Published: February 2008

IT is particularly appropriate to discuss Indium at a meeting of the Institute of the Aeronautical Sciences for it is in the aviation industry that Indium has received its greatest acclaim and has contributed so materially to the perfection of vital war machines. Indium in aviation is a reality and has long since passed the experimental stage and has become a vital factor in both power plants and airscrews.
Power‐Plant Efficiencies
Authors: Cleaver A.V.
Published: February 2008

ANY power plant used for propelling an aircraft at a steady flight velocity has an overall efficiency =η
Appreciation of Landing Problems
Authors: Drury G.W.
Published: February 2008

CASTORING stability requires automatic return, after displacement, of the castoring wheel to the central position. A hinged wheel may be automatically stable under static conditions, but dynamically unstable, or vice versa. Dynamic stability may be defined as the condition in which the forces on the wheel in motion secure its return to the path of direction of motion.
The Import Of Instruction Manuals
Authors: Kyd J.A.
Published: February 2008

INSTRUCTION books, like dentists, are there to be consulted, but people seldom go near either of them until things go wrong and then usually wish that a visit had been paid earlier. Like some dentists some instruction books are pleasant to consult. It is the aim of this article to show how all handbooks can be made interesting and consequently useful.
Testing Electrical Installations in Aircraft
Authors: Clark Arthur
Published: February 2008

MOST aircraft manufacturers would like to be able to check completely the functioning of all electrical installations while the aircraft is still in the rigging shop and without having to start the engines. Some tests, such as those for continuity of circuits and for “earths,” have for long been made at an early stage in the assembly; and much thought has, without doubt, gone on ways and means of increasing the amount of testing which can be done without running the engines.
Production and Maintenance section
Authors: Baker C.
Published: February 2008

AS the war becomes history and hostilities recede into the more distant past, much of the detail of events of the last six years is forgotten. Epics of great battles become classics; the Battle of Britain for example will ever hold a place of honour in history and the skill and speed with which the ground crews maintained and repaired the aircraft engaged will rank with the heroism of the air crews. But much of the normal routine work performed on air fields during the later stages of the war is liable to be overlooked, although a moment's thought reveals that without it our great bombing offensives could never have taken place.
The Inspection of Damaged Airframes
Authors: O'Halloran T.J.
Published: February 2008

ONE of the most difficult jobs in airframe repair is that of the inspector whose duty it is to detect and assess damage to the airframe structure, and this article is an attempt to review the many problems and difficulties with which he is faced when inspecting damage of the type caused by enemy action or heavy landings. I have not dealt with damage due to such causes as wear in moving parts, as their inspection is regularly undertaken as part of the normal maintenance routine and no new problems are likely to arise; crash‐landing damage, on the other hand, is generally a much more difficult job than enemy‐action damage from the inspector's point of view, and it is therefore dealt with at greater length.
Hawker Experience in Structural Repairs
Authors: Whittingham E.C. , Garrett Gisbert D.S.
Published: February 2008

IT was not until the Battle of Britain that Hawker Aircraft Ltd. found, like so many other aircraft firms, that pre‐war repair methods were unsuitable for dealing with the variety and quantity of work which resulted from large‐scale engagements in the air. They discovered that not only were new types of repairs needed but also that more attention had to be paid to the speedy distribution of repair information.
Hydraulic Systems in German Aircraft
Authors: Hodgson M.
Published: February 2008

HAVING disposed of the Messerschmitt hydraulic systems in the first part of this article, the remaining system of which details are given in C.I.O.S. report numbered XXXI‐41 is that of the Dornier 335. This aircraft was intended for use as a bomber or a day or night fighter and has a comprehensive hydraulic system, as is shown by the condensed symbolic diagram given in fig. 1. The system possesses several interesting features, both in the circuit connexions and in the design of the components.
The Bristol Method of Air Freight Handling
Authors: Davis J.H.
Published: February 2008

IT has been contended that from the operators' point of view air freight is preferable to passengers because of the inability to complain or be the cause of any of the minor troubles experienced with passengers, but in the past—at least so far as civil operations were concerned—air freighting as such has represented only a small proportion of the total loads carried by aircraft.
Stresses in Streamline Shells Due to Unsymmetrical Loading
Authors: Binnie A.M.
Published: February 2008

THE bending stresses in thin shells can often be neglected. If the loading on the shell is, for example, due to normal pressure or to gravity forces, the stresses due to strain in the middle surface of the shell usually outweigh in importance the stresses due to bending, which are small because the shell is taken as thin. The stresses can then be assumed uniform across the thickness of the shell, and, when calculated on this supposition, they are commonly known as membrane stresses. It is only in the neighbourhood of concentrated loads or restraints, such as rigid supporting rings, that significant bending stresses develop. But detailed analysis shows that these stresses rapidly die away, and beyond a short distance from the concentrated loading only strain in the middle surface need be considered.
German Variable‐Pitch Propeller Mechanisms
Authors: Grott S.
Published: February 2008

THIS report aims at giving a broad outline of German variable‐pitch propellers. Only the characteristic features and principles of operation arc described.
Downwash Behind Wings of Finite Span
Authors: Goossens E.
Published: February 2008

WHEN considering a flat plate of finite width at a low angle of attack, it is observed that, downstream from the plate, where the air flow from the suction and pressure sides join, a transverse velocity appears. On the pressure side there is an outward flow toward the ends of the plate, while on the suction surface the component is inward. Since all streamlines have the same origin, in the case of steady flow the pressure where the flow over upper and lower surfaces joins must be the same and no velocity ‘jump’ is possible. It follows then that any velocity change must be purely transverse and that this will extend to the ends of the plate. The same phenomenon occurs with wings of finite span and the vortices are formed continually in flight. These vortices absorb energy, for which power has to be supplied continuously—in other words the induced drag caused solely by the vortex formation appears.
Welding in the U.S. Aircraft Industry
Authors: Grimaud R.
Published: February 2008

THE importance of the electrodes has been realized in America and the number used is surprisingly large.
The Weathering of Moulded Plywood Components
Authors: Beaulieu L.A.
Published: February 2008

This Report of research work on moulded plywood for aircraft carried out in the Division of Mechanical Engineering, National Research Council of Canada, is published at the request of the Director.
The Library Shelf
Authors: Hemp W.S.
Published: February 2008

THE ‘Theory of Limit Design’ is a theory whose philosophy and methods will be familiar to most aeronautical engineers. The term ‘Limit Design’ may not be familiar and so it is probably necessary, before making com‐ments upon the theory, to give a short résumé.
The Stratofreighter Air Duct and Anticing Systems
Authors: Perry H.W.
Published: February 2008

THE U.S. Air Force recently ordered twenty‐seven C‐97 Strato‐freighters in addition to the thirteen previously ordered, some of which have been delivered. These are the cargo version of the Boeing Aircraft Company's Stratocruiser.
The Library Shelf
Authors: Phillips R.H.S.
Published: February 2008

Mr Rissik needs little introduction to engineers, least of all to readers of Aircraft Engineering, since much that is contained in his latest book on Quality Control was foreshadowed in articles published in this Journal during the war years.
The Oxy‐acetylene Welding of Aluminium and Its Alloys
Authors: Fitzgerald‐Lee G.
Published: February 2008

THE use of aluminium and aluminium alloys has grown to an enormous extent during recent years and there are few industries where aluminium docs not find a place. This paper is concerned with the welding of aluminium and its alloys by means of the oxy‐acctylene blowpipe flame.
Stability and Control of Single Rotor Helicopter with Hinged Blades
Authors: Zbrozek J.K.
Published: February 2008

THE present paper gives, in abbreviated form, the theory of blade motion and of static and dynamic stability of single‐rotor helicopters. Limitations of space do not permit of full discussion and the article should be taken as only an introduction to the somewhat complex problems of helicopter stability and control.
Some Aspects of the French Aircraft Industry
Authors: Charriou André
Published: February 2008

AT the present time, it is depressing to write an article on the French Aircraft Industry. At the end of World War I, it was the first in the world and the famous names of the illustrious air pioneers were still to the fore. Now, on the contrary, it is far behind the American, British and Soviet industries.
The Production of the Slingsby 21B Sedburgh Glider
Authors: Reussner J.C.
Published: February 2008

THE production of a glider presents problems that are similar in many respects to those found in the production of any other type of aircraft. The position in the case of the glider is simplified by the absence of such parts as the engine and the various equipment associated with it, and also the elaborate undercarriage installation. It is, however, complicated by the relatively large overall size of the aircraft as compared with an equivalent power machine.
Statistical Analysis of Experimental Data
Authors: Rossow E.
Published: February 2008

PROBABILITY paper was originally used to represent the summation curve of a Gaussian distribution as a straight line. Gibrat, Divisia in France and Daeves and Beckel in Germany have shown, that the summation curve of most skew distributions may also be represented as a straight line, if the argument x is traced as log (±x±a), where a is an arbitrarily chosen constant, which may, but need not, represent a physical condition.
A High‐Power Two‐Cycle Sleeve‐Valve Engine for Aircraft
Authors: Hiett G.F. , Robson J.V.B.
Published: February 2008

OVER a period extending from just prior to the outbreak of war until a year or so after D‐day, a continuous programme of single‐cylinder research was carried out by Messrs Ricardo & Co. Ltd., for the M.A.P.—now M.O.S.(A)—on the two‐cycle petrol‐injection sleeve valve engine. The account which follows is intended to give a description of this programme and of its results, but since the decision which brought it into existence was considerably influenced by preceding events, the sequence of these events is related briefly in order to present as complete a picture as possible.
Notes on Machining Stainless Steel
Authors: King R.H.
Published: February 2008

THE machining characteristics of the straight chromium and chromium nickel alloys depend upon:
The Slingsby Prefect Intermediate Sailplane
Authors: Reussner J.C.
Published: February 2008

IN the post‐war programme of Slingsby sail‐planes provision was made for the design of a 45 ft. span intermediate sailplane to be used for advanced training and as a general utility machine by gliding clubs. This machine appeared in the early part of 1949 and was named the Prefect; it has since been adopted by the R.A.F. as a standard training type under the designation of Prefect T.X. Mark I, Light Glider.
Stress Analysis with Brittle Lacquer
Authors: Salmon B.
Published: February 2008

First type isostatic lines: tangents at every point to the maximum principal deformation and stress, in algebraic values.
‘Pattern’ Cutting Curves for Inflatable Dinghies
Authors: Morris J.
Published: February 2008

THE buoyancy chamber of a pneumatic dinghy is roughly of ‘rubber inner tube’ form arranged around the wale or upper perimeter of the craft and when inflated the bow and stern ends are at a higher elevation than the midship section which is normally horizontal. The chamber is constructed of straight lengths of constant circular cross section each being joined to its contiguous members, the space curve of the contour of each joint constituting an ellipse. A requirement for the layout of the gores enjoins that the longitudinal scams of all portions should be outboard, continuous, rectilineal, and, as nearly as possible, in the relative positions they would occupy if the chamber were coplanar. A convenient plan by means of which this may be accomplished is to stipulate that the points of junction of the longitudinal seam lines of consecutive portions be in the plane containing the axes of assigned pairs of corresponding members and passing through the centres of the ellipses of junction of these members.
Aircraft Engineering Reference Sheet
Authors: Tonkin T.
Published: February 2008

The Marathon I (M.60) is an all‐metal, short/medium‐range aeroplane capable of carrying a maximum of 22 passengers or, by simple adaptation, freight and mixed cargo. Two flight crew (first pilot and second pilot/navigator) are carried; radio is installed immediately aft of the cockpit on the starboard side while directly opposite this location provision is made for a forward freight compartment or a seat for a third crew member. A toilet can be fitted on the left‐hand side of the passenger cabin just aft of the entrance door and a space at the rear on the‐right hand side can be utilized as a wardrobe.
Methods of Spiral Spring Design
Authors: Alexander B.
Published: February 2008

THE purpose of this article is to present a mathematical treatment which has been found extremely useful in the design of spiral springs since it enables us to determine the physical dimensions of a spiral spring, and also its behaviour when subject to a straining action; i.e. the change of the radius of curvature at any point, change in the number of coils or in the spacing of coils. The following method concerns itself only with the spiral springs whose coils throughout the whole range of deflexion are free, i.e. do not touch one another, and also the springs which become completely solid at the maximum deflexion.
Failure of Cylindrical Tubes Under External Pressure
Authors: Ringrose R.C.C.
Published: February 2008

UNDER external pressure cylinders fail in the following ways:
Thin Multi‐Walled Sections
Authors: Morse William
Published: February 2008

There is quite a lot of literature showing how to find the distribution of shear stress on a thin multi‐walled section under the action of an applied torque. In actual fact, however, before this torque can be assessed, it is necessary to know the position of the flexural axis of the section, the flexural axis being so positioned that when a shear is applied along it the section does not experience any torque. A method of finding the distribution of direct shear stress and hence the position of the flexural axis for a 2‐cell and then a 3‐cell section is explained.
Torsional Stresses in Multi‐Webbed Rectangular Cylinders
Authors: Mansfield E.H.
Published: February 2008

The determination of the torsional stiffness and shear stresses in a multi‐webbed cylinder is quite straight‐forward. However, if the number of webs is large (say, Ave or more) the calculations become tedious. This Note gives a rapid, approximate solution by utilizing the physical conception of spreading the internal webs out into an equivalent uniform web medium.
Electrical Circuits for Adding Strain Gauge Signals
Authors: Mansfield E.H.
Published: February 2008

Four electrical circuits for adding strain gauge signals in various proportions are considered and their relative efficiencies and sensitivities examined. The addition is effected by slight modifications to the Wheatstone bridge circuit. In all cases expressions are given for the galvanometer current, the sensitivity and the magnitude of any extra resisters in the circuit which are necessary to effect the addition; their derivations are given in an appendix.
High Temperature Combustion
Authors: Reichert Ing. H.
Published: February 2008

EXACT methods for thermodynamic calculations of high temperature combustion processes at equilibrium are very involved and time‐consuming because of the increasing influence of dissociation with increasing temperatures above 1800dcg. K. Many simplified methods have been proposed, but most of them are still rather complicated or approximate and are cither suitable for a special type of application only or based on assumptions valid within conditional limits. From the research engineer's point of view Mollier‐charts (total heat—entropy diagrams) would be most useful, but for general use too many charts would be required. For every possible reaction as many charts as there are mixture ratios have to be considered. Professor Lutz of Braunschweig proposed in 1947 a new type of enthalpy‐chart, which enables a wide range of applications to be covered by a reasonable number of charts. A number of such charts have been constructed by the Ministry of Supply.
The Touch‐Down Rate‐of‐Descent Indicator
Authors: Barasch Myles V.
Published: February 2008

DURING acceptance tests of aircraft, one of the basic data required is the rate of descent. The required information is a vertical component of the rate of descent just prior to touch‐down on a landing surface. These data are used as an aid in determining the impact imparted to the landing gear, as well as to other structures of the plane. Rate of descent information is also used during training of both military and commercial pilots. A pilot is interested in knowing immediately after touch‐down the rate of descent of his aircraft, so that he can associate his control settings and his psychological attitude with the data given him. The touch‐down rate of descent information is also important when hard landings aboard an aircraft carrier are considered. The deck of the carrier presents a second moving object with which to contend; therefore the rates of descent will be even more unpredictable and, in most cases, of higher values.
An Introduction to the Method of Characteristics
Authors: Harrop R.
Published: February 2008

The Method of Characteristics for two‐dimensional supersonic flow is developed from an elementary physical approach. Since the report is intended for use by those on supersonic research who have not advanced mathematical knowledge, the initial parts of the theory are given in greater detail than in many other treatments. In addition numerical examples are given to illustrate points more clearly. The relationship of the method to the Prandtl‐Meyer expansion of a supersonic stream round a convex corner is stressed and the theory of the expansion is developed from first priciples in the Appendix. The application of the method of characterisics to the design of supersonic nozzles is not fully discussed, but the constructional drawing of a typical nozzle is given, together with a photograph of characteristics obtained experimentally.
A Mollier Chart for Moisture‐Saturated Air
Authors: Reichert H.
Published: February 2008

This particular Mollier‐Chart has been constructed for investigations for increasing the power output of internal combustion engines and gas turbines by means of water injection into the supercharger or compressor respectively. Since the chart may be useful for other similar problems a short description is given and an example illustrates its application.
Laboratory Simulation of Kinetic Heating
Authors: Horton W.H.
Published: February 2008

This paper reviews and compares the methods of kinetic heat simulation which may be used simultaneously with normal loading in structural tests of aircraft or components. Basic data on the quantities involved in and the limitations of the various techniques are given. An extensive bibliography of current literature on heat technology is provided.
Thermo‐Elastic Similarity
Authors: Sobey A.J.
Published: February 2008

MODEL practice is sufficiently established in scientific investigations for the recommendation of its use in thermal stress analysis to be almost unnecessary. However, some of the reasons why models should be specified for an experimental programme are peculiar to thermal problems, while others are of a more general character.
The Present Position of Titanium in the U.S.A.
Authors: Carpenter S.R.
Published: February 2008

THE need for a high temperature material for the construction of supersonic aircraft has caused manufacturers to investigate the properties and behaviour of titanium. Convair of San Diego has carried out tests on titanium and compared the results with those obtained from other materials.
Aeroelastic Problems of Low Aspect Ratio Wings
Authors: Leyds J.
Published: February 2008

To determine the flutter speed, it is customary to introduce all factors into the Lagrange equations with the flutter speed as one of the variables. This paper deals with the energies to be substituted, and the ways and means to solve the problem. There are two distinct approaches to the solution, one which is well suited for calculation on digital computors, and one which is convenient for solutions by way of analogue computors.
Some Design Considerations for a Hydraulic Servo
Authors: Nightingale J.M.
Published: February 2008

PROMINENT among hydraulic servos today are those being developed in the aeronautical field, both for conventional aircraft and for guided missiles. In general these applications demand the following characteristics of the servos:
On the Mechanism of Fatigue
Authors: Shanley F.R.
Published: February 2008

THE paper by Thompson, Wadsworth and Louat on ‘The Origin of Fatigue Fracture in Copper’ contains much valuable information which, together with other recent work of the same nature, affords a basis for reviewing various theories concerning the mechanism of fatigue. In the light of recent information, it appears probable that the greatest road‐blocks in our progress toward understanding fatigue have been mental or semantic in nature. It is remarkable that a phenomenon of such importance has resisted solution for over 100 years, in spite of the tremendous amount of testing, papers and conferences that have been devoted to solving the problem.
The Fatigue Strength of Riveted Joints
Authors: Smith C.R.
Published: February 2008

IN the design of aircraft structures for fatigue strength, it is as well to bear in mind that those parts most likely to give trouble fatigue‐wise are those wherein rivets or bolts have to react a load. The term ‘react’ is used here to distinguish this from the case where rivets or bolts arc used to hold the skin on the frame, etc., where the worst possible concentration of stress in terms of the nominal gross area will approach that of a hole in an infinitely wide sheet, or about 3·0. The riveted joint is more likely to approach that of a lug, which, for conventional rivet spacing and edge distance would be about 5½ in terms of gross stress. In other words, our working stress for a joint would be about one‐half the axial stress in a plain sheet with holes for the same life. Other things, such as normal loads and buckling, may alter this ratio somewhat.
Practical Structural Design Problems of Supersonic Aircraft
Authors: Heath W.G. , Heath B.O.
Published: February 2008

BEFORE a detailed consideration of internal stresses may be made, it is necessary to define external loadings which are possibly critical. This involves the consideration of manoeuvres throughout the altitude range of the aeroplane, to a severity fixed by aerodynamic or specification values of speed and normal acceleration.
Stability and Control Problems of Supersonic Aircraft
Authors: Michaelson O.E.
Published: February 2008

IN the past, the required amount of directional stability was dictated mainly by asymmetric power considerations and by the maximum angles of sideslip in manoeuvres permissible from the structural strength viewpoint. The requirement for satisfactory recovery from steady spin would in certain cases influence both the directional stability and control power in such a fashion as ultimately to be the determining factor. Present indications are that the choice of the required degree of directional stability will be based on supersonic lateral dynamic stability considerations, in particular the stability of the so‐called Dutch roll oscillation, or on considerations of avoiding inertia coupling between the lateral and longitudinal degrees of freedom during rolling. Both of these problems will be discussed in some detail later. It should be emphasized, however, that large values of subsonic directional stability will be required for supersonic aircraft in order to provide satisfactory dynamic characteristics at supersonic speeds at high altitudes.
An Analytical Investigation of Creep under Combined Loadings
Authors: Narasimhamurthy P.
Published: February 2008

BISPLINGHOFF has given a comparative graph showing the relative importance of the parameters of design at various Mach numbers. At Mach numbers above five, i.e. in the range of missile flight, creep becomes the critical design factor. Even though the time of flight of the missile is very short, and not enough to cause any considerable amount of creep, the deflexions caused will be enough to disturb the stability of compression members. Also the aerodynamic shape can be distorted with serious effects on the flow characteristics of the profile.
Measurement of Adhesive Moduli
Authors: Tapp P.F. , Broodo A. , Horn C.E. , Castner S.V.
Published: February 2008

MANY efforts have been made to evaluate adhesion by relating adhesion to measured forces. Many of these are comparative and do not actually measure adhesion alone, but depend upon some related property of the adhesive film—such as toughness, cohesion, brittleness, hardness or elasticity.
Wind‐Tunnel Interference Due to Model Supports
Authors: Pankhurst R.C.
Published: February 2008

IN Aircraft Engineering for October 1956 (p. 362) Lockwood Taylor discussed the wind‐tunnel interference arising from model supports and their guards, and gave a theoretical analysis for the contribution due to the flow curvature induced at the model and that due to the increment in longitudinal velocity (solid blockage). Both these are potential‐flow effects.
The Library Shelf
Authors: R.H.M.  , D.B.S.
Published: February 2008

This book should serve as an admirable introductory text: it is very well written and organized and the approach adopted is sound. Nowadays, when a book on servomechanism theory appears almost monthly, one has misgivings at the publication of yet another one, particularly as many of the American texts are practically indistinguishable from each other. However, the book under review has a character of its own, which would make it form a suitable basis for a university course.
Fourth Annual National Forum of the American Helicopter Society
Authors: Payne P.R.
Published: February 2008

THE wise conventioner strives to become something of a connoisseur if he is to avoid a combination of dreary lectures and oppresive heat or cold.
Dilution of Cryogenic Liquid. Rocket Propellants during Pressurized Transfer
Authors: Greenfield S.
Published: February 2008

IN the testing of rocket engines and engine components, such as thrust chambers and gas generators, the rocket engineer is regularly faced with the job of transferring cryogenic liquid propellants, using pressure feed from a storage tank, through a flow system and into the combustion device to be tested. At Rocketdyne, liquid oxygen, LOX, is quite commonly used as a propellant, and in the testing of engine components inert pressurants are usually used, for example, helium or nitrogen, although because of the cost and logistics, nitrogen is preferred. When gaseous nitrogen is used as the pressurant, we have repeatedly run into testing conditions which have resulted in condensation of nitrogen and subsequent mixing in the tanked liquid oxygen. This dilution of the liquid oxygen effects a loss of performance and imposes mechanical difficulty in maintaining a regulated propellant tank pressure.
Effects of Local Loadings on Pressurized Circular Cylindrical Shells
Authors: Klein Bertram
Published: February 2008

An analysis is carried out to determine the deflexions and stresses in the region of a highly localized loaded area of a circular cylindrical shell initially subjected to internal pressure. Four types of loading are considered: uniformly distributed radial loading, linearly distributed longitudinal bending moment, linearly distributed circumferential bending moment, and uniformly distributed tangential loading. There are five basic parameters defining the structure and loading. Results are presented in the form of diagrams for the first three cases and a table for the last.
The Analysis of Fuselages of Arbitrary Cross‐section and Taper
Authors: Argyris J.H. , Kelsey S.
Published: February 2008

A DSIR Sponsored Research Programme on the Development and Application of the Matrix Force Method and the Digital Computer. The present issue gives a summary of the basic theory of the matrix force method together with some necessary extensions for the fuselage problem. The equilibrium conditions for the idealized structure are then examined in detail and the relevant equations of equilibrium established in matrix form.
Anti‐Vibration Mounting of Aircraft Power Plants
Authors: Harriman J.F.
Published: February 2008

THE engine and propeller when installed in an airframe transmit various loads to the aircraft structure through the engine mounting. These can be grouped as follows:
The Library Shelf
Authors: E.L.J.  , A.D.B.
Published: February 2008

The publication of A Handbook on Torsional Vibration by the British Internal Combustion Engine Research Association, marking as it must the culmination of a phase of the work of the torsional vibration panel, may be considered a significant milestone in its history.
Power for the Long‐Range Supersonic Airliner
Authors: Jamison R.R.
Published: February 2008

IN investigating what powerplants will best meet the needs of the long‐range supersonic airliner we have to postulate that there will be such an aircraft and we need further to have some idea of its nature to match the engines to it, while equally, if we think about it, the kind of engines which could be available will react on the design of the airframe. So it appears that we must look at these two fields at first separately and then jointly in order to evolve a design specification for the complete aircraft. Moreover, the whole conception of a modern commercial aircraft has become so complex, in meeting a great diversity of operational requirements, that even in the fairly narrow process of matching the airframe and its engines a wide range of factors must be taken into consideration.
The Control and Stability of Hypersonic Aircraft
Authors: Nonweiler T.R.F.
Published: February 2008

THERE have been various suggestions that the return of man from his trips of exploration into space may best be effected by glider. The design of such an unusual form of aircraft will present many unusual and difficult problems, and here we shall merely be content to remark upon those which fall into the category of stability and control.
Creep Deformation
Authors: Saroja Mrs B.V.
Published: February 2008

AN analysis of creep deformations in rotating disks of constant and variable thicknesses by experimental and theoretical methods, has been presented by Wahl and his collaborators in a series of papers. Wahl first based his theory on the Mises Criterion and found that it gave creep deformations which were too low compared to the test‐values. Later he carried out his investigations using, in the first instance, Maximum Shear Theory with the flow rule associated with Mises Criterion and in the second, the Tresca Criterion with its associated flow rule, assuming zero radial‐creep‐strain rate. He has concluded that better agreement between the test and theoretical values could be obtained in the later cases.
The Library Shelf
Authors: J.J.S.  , A.D.B.
Published: February 2008

This book gives an up‐to‐date account of the principal methods of analyzing the aerodynamics of missiles. It collates the theories and results of the many technical reports on the subject which have been written in the last fifteen years and gives a clear indication of their applications and limitations. The author assumes that the reader has a fundamental knowledge of theoretical aerodynamics, particularly of fluid motion and develops from this the various theories and results which are particular to missile problems.
Vibration of Missiles
Authors: Cox H.L.
Published: February 2008

The free and harmonically forced flexural vibrations of missiles resting on fixed or mobile launch platforms are considered. A general matric formulation is given for the problem in which the effects of variable boundary conditions at the base support, variable axial loads along the missile length, variable stiffness and material properties, variable mass, variable mass moment of inertia, variable shear stiffness, and variably distributed forcing functions are treated. The problem is matrically formulated in standard eigenvalue form, and no special coding should be required for organizations that are currently solving eigenvalue problems on electronic digital computers. For a particular problem only fundamental data are needed for filling in the element locations of the matrices involved, and almost all calculations are performed within the computer. The matric formulation presented herein is also valid for partially and completely restrained cantilever beams.
The Analysis of Fuselages of Arbitrary Cross‐section and Taper
Authors: Argyris J.H. , Kelsey S.
Published: February 2008

A series of examples illustrates the application and results of the method previously given for improving the conditioning of the primary redundancies. The transformation matrix giving locally orthogonal redundancies for the parent station is used also to generate the primary self‐equilibrating stress systems for sections with different (but related) geometry and varying ring stiffness. A double‐cell cross‐section is also treated and a brief investigation shows that the general methods developed for establishing primary redundancies in the fuselage can be usefully and economically applied to certain kinds of wing structure. Preparatory to a detailed discussion of cut‐outs and modifications in the fuselage structure, the necessary general theory is collected and summarized.
Constant Speed Drives
Authors: Mooney J.P.
Published: February 2008

MODERN turbojet engines have a shaft speed range of approximately 2 to 1 (from ground idle to take‐off) and it is necessary, therefore, to have some form of infinitely‐variable‐ratio gearbox to obtain a constant speed for accessories such as a.c. generators. Various means of doing this are available; for example, these could be mechanical, electrical, hydraulic or pneumatic, or a combination of these. The purpose of this paper is to discuss the major types of constant speed drive (C.S.D.) that have been evolved, mentioning the design problems associated with each.
Correcting Fatigue Life Inadequacy
Authors: Smith C.R.
Published: February 2008

WHERE service life, cither actual or simulated, has proven to be inadequate, the need for a simple conversion of fatigue cycles to service life is paramount. The task becomes exceedingly difficult in the case of service life where neither number nor magnitudes of loads can be determined. The only known quantity is that the machine or structure lasted only one‐tenth, one‐third, or not quite as long as it should.
Aviation Fuel Problems
Authors: Goodger E.M.
Published: February 2008

In the case of stationary fuel tanks subjected to high ambient temperatures for prolonged periods, vaporization may account for a significant loss of the more volatile fractions. Although the quantitative loss might not be serious, fuel quality may be affected to the extent of difficult starting under subsequent low temperature conditions.
Filtration of Aircraft Hydraulic Systems
Authors: Harcourt R.A.G.
Published: February 2008

FILTERS have been in use in one form or another throughout history. Despite this fact, there has been, until comparatively recent times, very little written upon the subject. Certainly, to the author's knowledge, there has been only a handful of papers written or read upon high‐pressure oil hydraulic filtration within the past decade. It was for aircraft hydraulic circuits that Fairey originally designed filters and only then because the Company failed to find a filter that fulfilled the stringent requirements we set down as representing the minimum standard demanded by our own hydraulic systems.
Teaching Aircraft Design
Authors: Newell A.F. , Howe D.
Published: February 2008

Aircraft Design has been taught at the College of Aeronautics since 1946. The course is at postgraduate level and is of two years' duration. In the first year the students are given three exercises in component design which aim to teach a logical approach and the fundamentals of the subject. During the second year each student works as a member of a team engaged in the design of a complete aircraft, which is chosen to be of a type currently being investigated by industry. The project aircraft invariably incorporates experimental features and the design work is therefore of the nature of research.
Present and Future Developments in the Use of Organic Materials for Aircraft Transparencies
Authors: Crick R.D.
Published: February 2008

The use of organic materials in the construction of aircraft transparencies is introduced by discussing their properties in relation to the requirements of strength and vision of the different types of transparency in the variety of environmental conditions in which they have to operate. The advantages and disadvantages of the particular currently manufactured materials are examined and the way in which their individual properties may best be utilized in the design and construction of transparencies is described and demonstrated by showing examples of proven designs. Present and future developments of both rigid sheet and flexible interlayer materials are discussed, particular reference being made to the development of ‘high temperature’ materials and the use of plastic main plies in combination with glass face plies to form hard‐wearing lightweight laminates. With the present availabilty of the improved acrylic materials, the author looks forward to the possibility of a reduction in the required design factors and a change in the interpretation of the fail‐safe requirements enabling simpler, lighter windows using organic materials to be designed in the future.
Design Considerations for Recent American High‐Performance Manned Flight Vehicle Transparencies
Authors: Shoemaker A.F.
Published: February 2008

The factors which should be considered when contemplating windshield design are outlined, and various levels of high performance vehicles are defined. The relationship between environment and design criteria is discussed and the author introduces some of the unique glasses in current use.
Alleviation of Thermal Stresses in Bi‐metallic Spar Webs
Authors: Przemieniecki J.S.
Published: February 2008

Results of an Investigation to Determine the Effectiveness of a Bi‐metallic Construction on Four Three‐spar Box Specimens Subjected to Simulated Aerodynamic Heating. The maximum thermal stresses in a stainless steel skin‐web combination subjected to aerodynamic heating may be greatly reduced by the addition of a thin layer of aluminium or copper to the stainless steel web. Such bi‐metallic construction increases the rate of conduction of heat from the structural parts (skins) exposed to the aerodynamic heating to the non‐exposed parts (webs) and consequently this produces a reduction in temperature gradients and thermal stresses. This paper presents the results of an investigation to determine the effectiveness of a bi‐metallic construction on a three‐spar box specimen subjected to simulated aerodynamic heating. The tests confirmed the feasibility of the method and indicated that the theoretical calculations give sufficient accuracy for design studies, provided an estimate of the joint conductance can be made. The method is effective only for relatively low heating rates and shallow wing structures. The work reported in this paper was sponsored by the Aerospace Research Laboratories, Wright‐Patterson Air Force Base, Ohio, under project No. 7063, Task 706302.
Medical Evaluation of Airmen exposed to Supersonic Transport Altitudes
Authors: Barron Charles I.
Published: February 2008

This paper describes an investigation into the ability of man to withstand the environmental stresses existing at the high altitudes associated with supersonic flight. The medical histories of a group of pilots who had been exposed to altitudes in excess of 50,000 ft. were compared with those of a control group whose flying had been confined to normal altitudes. The total exposure time of the test group was estimated to be in excess of 35,000 hours. Dr Charles I. Barron is the Medical Director of the Lockheed‐California Company. He is a graduate of the University of Illinois College of Medicine, and he served as a flight surgeon in the Army Air Corps during World War II. He has been engaged in extensive research work and has published numerous papers on the effects of aircraft noise, microwave radiation, escape systems, decompression, and on various aspects of human engineering. He is a past president of the Aerospace Medical Association and has served on the National Research Council Committee. At present, he is the Chairman of the Research Advisory Committee on Biotechnology and Human Research for N.A.S.A. and Chairman of the Medical Advisory Council to the Federal Air Surgeon. He is a lecturer in aviation physiology in the Aerospace Safety Division at U.S.C., and an Associate Professor of Aerospace Pathology at U.C.L.A.
Short Take‐off and Landing for High Speed Aircraft
Authors: Wimpress John K.
Published: February 2008

THE shortened runway has become an order of the day. Commercial operators want to offer jet service to communities with small airports. Military services seek to use small, unprepared fields—or no fields at all, just clearings.
An Approach to Economic Space Transportation
Authors: Smith T.W.
Published: February 2008

THIS paper represents the personal views of the author and the objectives do not necessarily form any part of current official thinking.
Farnborough on the Fiftieth Anniversary of the S.B.A.C.
Authors: Wynn Humphrey
Published: February 2008

OUTWARDLY, this month's Flying Display and Exhibition organised by the Society of British Aerospace Companies will probably look very much like its predecessors at Farnborough: rows of tented manufacturers' enclosures on the green hillside over‐looking the runway; a vast exhibition hall with assorted missibles pointing skywards outside it; thousands of foreign visitors, many of them in uniform, on the trade days; a flying programme in the afternoons, with aircraft taking‐off and landing so strictly to time as to form a continuously changing pattern of different types; and on the public days, crowds of up to a hundred thousand.
Sonic Boom and the SST
Authors: Thompson Jim R. , Parnell John E.
Published: February 2008

SONIC boom is the name which has been given to the sound heard on the ground immediately following the passage of an aircraft overhead at supersonic speeds. This sound, which has been compared to nearby thunder, results from the passage of the aircraft's shock‐wave field over the observer.