bluuebunny/crossref_metadata_2025_split huggingface dataset:
The tip flow of a part span slotted flap
Authors: Willmer A. C. , Barrett R. V. , Coleman J. D. 
Published: July 2016

The work to be described forms part of an experimental study into the overall influence that the end region of a flap has on the flow of a high lift wing system. Here, our attention will be restricted mainly, but not entirely, to the tip flow of the flap itself.The study has been a collaborative venture over the past three years between British Aerospace-Civil Aircraft Division and the Aerospace Engineering Department of Bristol University, the latter funded by an SER.C research grant. BAe's major contribution was the undertaking of the main test programme, with University participation, using a large swept wing, high lift half model in the Filton low speed wind tunnel. The model was loaned by RAE for the study.
Recent Evolution in Problems and Methods in Aerodynamics
Authors: Germain P. 
Published: July 2016

The Tenth Lanchester Memorial Lecture “Recent Evolution in Problems and Methods in Aerodynamics” was given before the Society on 11th May 1967 by Professor Paul Germain, Director General of ONERA. The Chair was taken by the President, Mr. M. B. Morgan, CB, MA, CEng, FRAeS.Opening the proceedings the President said that they had had a memorable series of lectures in memory of that great man Lanchester and at many of them it had been a great pleasure to have with them his widow, and his brother Mr. George Lanchester and his wife. They were delighted to have them present that evening.They were fortunate to have as their lecturer Professor Germain, a distinguished French Scientist. It was particularly appropriate that their lecturer should come from France when Franco-British aeronautical ties were already close. Professor Germain was well known to the aeronautical research fraternity. Born at St. Malo in 1920, after graduating in Paris he joined ONERA and later became Professor at, first, Poitiers, then Lille and Paris. Since 1962 he had been Director of ONERA. His theoretical work in the transonic and supersonic aerodynamics fields was well known and they also knew him well personally because he had paid numerous visits to research centres in this country.Professor Germain was France’s National delegate to AGARD and Mr. Morgan knew from personal knowledge the intense interest Professor Germain had taken in that international organisation. He held an Honorary Doctorate from Louvain University, was a Correspondent of the Academy of Sciences, Paris, a Fellow of the American Institute of Aeronautics and Astronautics, a Foreign Honorary Member of the American Academy of Arts and Sciences and a member of the International Academy of Astronautics.
Buckling and Vibration of Triangular Flat Plates
Authors: Lockwood Taylor J. 
Published: July 2016

Summary:—Simple exact solutions have been tound for the modes of buckling or vibration of an equilateral triangular plate with supported edges. They may be classified as 1 (a)—modes symmetrical about all three medians, 1 (b)—modes symmetrical about one median, 2—modes anti-symmetrical about one median. Mode 2 obviously also covers the modes for a 60° right-angled triangle forming one half of the equilateral triangle. The frequency for each mode of type 2 duplicates that for a corresponding mode of type 1(b).
Technological Progress and the Airlines
Authors: Shaw R. R. 
Published: July 2016

One of the few privileges the public lecturer has is to divide all mankind into two classes according to his prejudices, and this I intend to do: on the one hand those restless souls who constantly strive for innovation and change; on the other the great mass of humanity who resist and even resent any disturbance of the even tenor of their ways.The first fish-like beast that crawled out of the primeval swamp on to land must have had something of this spirit of change and adventure. And from the dawn of history the rare men with these characteristics have provided the leadership and sparked the changes that have been at the heart of human progress.
Comments on “Transient Temperatures and Thermal Stresses in an Idealised Wing Structure“
Authors: Johns D. J. 
Published: July 2016

In ref. 1 an analytical solution was given for the one-dimensional distribution of temperature in a web of an idealised, symmetric, multi-cell wing structure when symmetrically heated. It was assumed that the convective heat transfer coefficient, h, was constant, but the adiabatic wall temperature variation was assumed to be either an instantaneous or a linear function of time.The purpose of the present paper is to indicate the application of an alternative, approximate method of heat flow analysis due to Biot and to show thereby how the usefulness of the results in ref. 1 can be extended by eliminating the assumption therein that the skin temperature was uniform at any given time. The notation of ref. 1 is used with additions as defined in the paper.
Handling Criteria
Authors: O'hara F. 
Published: July 2016

SummaryThe nature of handling criteria and their uses in relation to the prediction of aircraft handling characteristics are discussed. A brief history is given of the development of ideas on handling, and a survey is made of criteria for modern aircraft, looking particularly at the physical factors affecting the pilot, as an indication of the basis of the criteria. The novel handling features arising with new aircraft species like slender wings and VTOL are considered. The scope of flight simulators and variable stability aircraft for systematic study of handling is discussed and the potentialities of theoretical study by means of servo analysis techniques considered. Finally, possible lines of development in relation to the assessment of aircraft handling characteristics are suggested.
A Thin Aerofoil of Small Camber in a Non-Uniform Flow
Authors: Nigam L. N. 
Published: July 2016

The direct problem of aerodynamics (profile of the aerofoil is given—calculate the aerodynamic characteristics) has been studied for thin aerofoils with small camber. Given the undisturbed stream functionV, ω, α being the constant velocity, vorticity and angle of incidence respectively, the pressure distribution, lift coefficient and pitching moment have been calculated for a general profile.
Beryllium
Authors: Leadbeater C. J. 
Published: July 2016

Beryllium is a metal possessing some attractive properties for aerospace applications, but its advantages are offset by the present inability to achieve acceptable isotropic ductility, by the high cost of the fabricated metal and by the special health precautions required for workshop treatments and handling.Considerable research and development have been applied to the technology of beryllium during the past decade and comprehensive data are available in books and the proceedings of international conferences held in London, Gatlinburg, Philadelphia and Grenoble. Outstanding among the various problems discussed have been modes of deformation and fracture, the efficiency of various methods of purification and the influence of increased purification on the behaviour of the metal.
Wire Reinforced Metal Composites
Authors: Forsyth P. J. E. 
Published: July 2016

The strength of a composite material will depend sensitively on that of the fibre chosen for reinforcement. Metallic and non-metallic whiskers can be very strong and other less strong, but more practical, fibres such as carbon, silica and boron are now available in experimental quantities. Some of the non-metallic whiskers, and the last three fibres mentioned, will no doubt eventually be made on a production scale.The strongest drawn wires yet available have tensile strengths of more than 0.5 X 106 psi which is still only one-third of that of iron or sapphire whiskers, and compares with boron in filament form, although the specific strength of the steel wire would only be one-third of the latter. On the basis of specific strength drawn beryllium wire would be only slightly better than the steel, but would have about 6 times its elastic modulus (E) which is comparable to that of boron.
Post First World War
Authors: Fell L. F. R. 
Published: July 2016

I returned to England in February 1919 to take over the duties of Assistant Director of Research and Development (Engines) under Brigadier-General Brooke-Popham, who was appointed Director of Research about the same date.At that time it was anticipated (correctly) that there was no danger of another major war for at least ten years and the staffs of the Royal Air Force and the Air Ministry were cut down drastically to suit. The Engine Research and Development departments which had employed many hundreds during the war were reduced to about a dozen people. While this was being done the engine position as it existed was being examined. It soon became obvious that none of the engines which had been in production during the war were suitable for further development to meet the requirements of the 1920's.
Effects of an Initial Gap on the Flow in a Turbulent Wall Jet
Authors: Sridhar K. , Tu P. K. C. 
Published: July 2016

SummaryThe flow in a two-dimensional plane wall jet with different initial gaps between the nozzle exit and the leading edge of the wall was probed at various stations along the jet. The jet slot thickness and the velocity were kept constant. It was found that the region close to the leading edge of the wall behaved like a transforming region where the type of flow changed from a free jet to a wall jet. The length of this region, which depended directly on the gap size, was so short for small gaps that the gap effects were found to be negligible. In addition, it was found that the inner layer velocity distribution of a wall jet did not follow the classic one-seventh power law.
Plowden and the Man in Industry
Authors: Davies S. D. 
Published: July 2016

This article is intended to examine the Plowden Report as it affects the man in industry—is there a future for him, where will he go and what should he do? This is obviously a matter of vital importance to members of our Society and it is hoped that what follows will be constructive, although it is written in the atmosphere of an impending General Election with an apparent hiatus in any constructive thinking in Government circles on the matters which affect us most.The appointment of the Plowden Committee was regarded by many people in the industry as an earnest of the Government's intention to end the waffling and indecision which has plagued us for many years.
The Application of Dynamic Programming to the Design of Invariant Auto-Stabilisers
Authors: Dyer P. , Noton A. R. M. , Rutherford D. 
Published: July 2016

SummaryIn the past decade considerable attention has been given to the possibility of using self-adaptive control systems to cope with the problem of providing stability augmentation to aircraft over extended flight envelopes. On the other hand, it has sometimes been considered that insufficient attention has been given to the design of autostabilisers with fixed parameters. The authors have applied recent developments In dynamic programming to the design of aircraft autostabilisers. The methods provide a highly systematic approach to the design of multi-loop systems which is especially useful for control of the lateral mode. Furthermore, the resulting optimum multiple feedback coefficients vary little throughout the flight envelope and the use of fixed parameters for the whole of the flight envelope appears to be possible. Aerodynamic data for two aircraft were used: a supersonic VTOL aircraft and a supersonic transport.
Body-Wing Interference at Supersonic Speeds
Authors: Phythian J. E. 
Published: July 2016

SummaryA summary of available information on the problem of body-wing interference in supersonic flow has shown, inter alia, that a large number of theoretical methods are available for the prediction of interference characteristics. Many of these methods are chiefly concerned with the estimation of overall characteristics,i.e.normal force and pitching moment. Several methods are available to determine the pressure distribution for restricted types of configurations, but these often involve lengthy computation.It is the aim of this paper (Part I) to summarise a simple yet reasonably accurate method of estimating the pressure distribution and hence (in Part II) the overall characteristics of as general a body-wing configuration as possible. The method which applies essentially to a cropped-delta wing symmetrically mounted on a cylindrical body, achieves reasonable accuracy without considerable computational effort; it is based on certain theoretical results together with empirical modifications. The results for pressure are generally valid up to an angle of incidence, α=6° —8° and in some cases for higher values of α. The overall normal force and centre of pressure position should hold up to α= 10°.
The Present Situation The State of Affairs in the Royal Air Force
Authors: Nance C. T. 
Published: July 2016

Over the past ten years the RAF has cost the country an average of some £500 m per year. Of this sum about £200 m has been spent with the aircraft and electronic industries, of which about half has been for new aircraft and weapons, the remainder being needed for spares, modifications and ground equipment. A further £200 m is expended on service and civilian manpower, the majority of whom have been employed on the maintenance of technical equipments or are needed to provide direct support for personnel so employed. Thus we have a situation where something like £200 m a year—almost half of the total budget—is spent upon maintenance.As the cost of modern weapons systems needed to achieve the necessary operational performance is increasing rapidly, the front line strength of the Royal Air Force will be weakened unless substantial savings in these maintenance costs can be made, and this in the face of increasing complexity of aircraft equipments.
The Safety and Reliability of Complex Systems
Authors: Lloyd E. 
Published: July 2016

I Would like to describe an approach which is being made by the Air Registration Board to the Safety of complex systems such as those used in automatic landing, or in supersonic and other advanced aircraft, since I believe that these methods may have a further application in the assessment of aircraft reliability.Airworthiness Requirements can be considered to be of two kinds. There are empirical requirements based on engineering interpretation of past experience, and there are those which stem from a selected level of safety and which involve consideration of probability of occurrences. This paper is concerned with the second kind since it is relevant to the consideration of reliability.
Lessons from Engine Experience
Authors: Bowling A. G. 
Published: July 2016

First let us look at the history of our engines’ reliability. Fig. 1 shows the reliability in terms of unscheduled removals per 1000 hours and in-flight shut-downs for four Rolls-Royce civil engines since the time of their introduction into service.It is significant that the general trend is similar and particularly, that after the initial years settling down period, the level of reliability defined in this way has stayed almost constant, despite considerable increases in overhaul life and, for the Dart, great increases in power output as later types of engine were produced.
An Empirical Formula for Stagnation Point Velocity Gradient for Spheres and Circular Cylinders in Hypersonic Flow
Authors: Topham D. R. 
Published: July 2016

When stagnation heat transfer rates are expressed in terms of free stream flow properties, the following combination of terms is found to occur: —where ps pressure at the stagnation pointp∞free stream pressureU∞free stream velocityDnose diameterßstagnation point velocity gradient.
Assessment of Thermal Fatigue Resistance of High Temperature Alloys
Authors: Barnes J. F. , Tilly C. P. 
Published: July 2016

This note is concerned with the significance of a “hold period” on thermal fatigue endurances and on the use of a frequency exponent to correlate the results of mechanical fatigue tests at various temperatures.In their note in the January 1965 Journal (pp. 53-55), Coles and Skinner quite rightly pointed out that residual stresses, set up as the result of plastic yielding in compression during an initial heating period, will undergo redistribution during a subsequent “hold period” at an elevated steady temperature. However, it is important to note that the redistributed stress pattern and the associated creep strains at the conclusion of the “hold period” will depend very much on the nature of the applied loading. For example, the compressive strain and the associated tensile stress set up in the rim of the disc will both fall in magnitude if the disc is not rotating and may reach infinitesimal values if the “hold period” is long enough.
Free Vibrations of a Circular Plate
Authors: Gajendar N. 
Published: July 2016

The Free and damped vibrations of a circular plate with given initial conditions, which is either free or elastically restrained along its outer edge, are discussed using the method developed by Reid and some numerical results are also given.The vibration of a circular plate has been studied considerably and most of the authors seem to be interested in determining the frequencies of vibration and the nodal patterns. A few investigators have studied the problem of determining the subsequent motion of a thin plate started with some given initial displacement or velocity. Sneddon has attempted this problem, taking into account an approximate boundary condition. Recently Reid has discussed this problem without taking recourse to any approximate boundary condition. He has developed a method of analysis to determine the displacement of a freely vibrating thin circular plate with the given initial conditions, using the norm of the eigen functions.
A Correlation of Leading Edge Transition and Heat Transfer on Swept Cylinders in Supersonic Flow
Authors: Topham D. R. 
Published: July 2016

Summary:—It is shown that stagnation line heating rates for laminar, transitional and turbulent boundary layers measured on swept cylinders at supersonic speeds, can be correlated in terms of a Reynolds number based on the spanwise momentum thickness at the stagnation line.A critical Reynolds number for transition along the stagnation line is determined and experimental results show evidence of transition up to M= 10.
Aeronautical Research and Development in the Commonwealth
Authors: Woodward-Nutt A. E. 
Published: July 2016

“Tadpole and Taper were great friends. Neither of them ever despaired of the Commonwealth.” Disraeli—“Coningsby”.In looking through the list of British Commonwealth Lectures one finds that the great majority deal with the work or problems of a particular country. There are few which deal with the Commonwealth as a whole, the outstanding exception being the remarkable paper on Aviation and the Development of Remote Areas given by H.R.H. the Duke of Edinburgh in 1954.
The Manufacture of Aerofoil-Section Blades for use in a Cascade
Authors: Clayton B. R. 
Published: July 2016

SummaryA method is described by which blades of aerofoil section can be manufactured on a laboratory scale. Emphasis has been placed upon cheapness, rapid production, and the ability to obtain an accurate representation of the blade profile for a large aspect ratio of 3·5. In addition, for a series of experiments with a cascade in water, the blades were to be made from a material which did not require the use of a protective paint on the surfaces. To satisfy the above requirements a casting process was adopted, and the blades were made from a plastic resin material. Although the discussion presented is confined to the production of blades, the method can easily be extended to the manufacture of impeller hubs, fairings, nozzles, and so on.
Snap-Through Buckling of Thin Arched Ribs
Authors: Creighton A. J. , Tee R. S. 
Published: July 2016

Structural failures have been experienced recently in some panels of relatively thin plating, dished to about twice the plating thickness, and failure has been attributed to snap-through buckling.Snap-through buckling may be defined as the lateral instability of a dished panel when loaded on the convex side. (Such an effect js frequently observed in the lids of biscuit tins.)
From Ship-Accompanying Waves to Shock Waves of Supersonic Aeroplanes
Authors: Legendre Robert G. 
Published: July 2016

When I was invited to deliver the Lanchester Memorial lecture, I wondered why the great honour of being the first Frenchman selected for the celebration of the deeds of a great engineer was conferred on me. However, I am well aware that the Council of the Royal Aeronautical Society cannot make a mistake and there is good reason to choose, after so greatly famed professors, an engineer of the French Navy to illustrate, using a slightly different point of view, the influence of Lanchester on the development of aeronautics. This way, I do not have to apologise for a possible inadequacy which then would not be my own responsibility. I have only to do my best, so as not to betray the confidence of the Society.
Answering so plainly this first question, I had to find out how to fulfil my task. Possibly, my contribution to the intrepretation of the vortex sheets starting from the thin leading edges of a delta wing is more in the Lanchester line of thought than it is an extension of Prandtl’s inferences.
Structural Weight Estimations for Novel Configurations
Authors: Burt M. E. 
Published: July 2016

SummaryThe aims of structure weight estimation are discussed and a review is given of its development in this country during the past fifty years from the simplest of formulae to quite detailed methods. The limitations of formulae derived only from statistical analysis of actual aircraft structures are noted. For aircraft of novel configuration it is essential for the weight of the basic load-carrying structure to be estimated by methods which are based upon the actual design and stressing procedures. The principles of “optimum” or “minimum-weight” structural design are a valuable feature of such methods and are briefly described. Statistical analysis, however, is still important for estimating the substantial weight of the joints, cutouts, transparencies and other features which transform a theoretical optimum structure into a complete and practical one. The problems of several aeroplane and missile configurations of current interest are discussed, and also the extent to which detailed design work is necessary to provide reliable structure weight estimates for such projects.
When Aeronautical Science was Young
Authors: Taylor Geoffrey 
Published: July 2016

It is Always rather risky to ask old people to talk about what things were like when they were young. Having turned on the tap you may not see how to turn it off again. Fortunately there is a circumstance which keeps this trouble under control. Old people remember a lot of things when there is no call for them to do so but seldom when there is. That is the reason why I have written down most of what I can say for this lecture.I cannot attempt to give a complete or an objective picture of aeronautical science when I started thinking about it. The best I can do is to describe a few of the things which happened to me in those days to try to convey some picture of our primitive ideas.
Aircraft Engine Developments During the Past Half Century
Authors: Nixon Frank 
Published: July 2016

As was said of Richard Trevithick, “Practical men are too apt to leave facts unrecorded”, and this is particularly true of those involved in the development of Britain's aircraft engine industry.The names of a few people come to mind immediately, but there are others whose contribution has played a crucial yet barely-recognised part in directing the overall trend. In addition there are many others who have filled lesser but vital roles as members of the teams led by the better-known pioneers.Source-material on which to base an account of the work of Society members is scanty, since the great majority of published papers have preserved that strict anonymity which is indicative of British “team spirit”.