bluuebunny/crossref_metadata_2025 huggingface dataset:
The Conflict between the Irish Administration and Parliament, 1753–6
Authors: McCracken J. L.
Published: August 2016

The history of eighteenth-century Ireland prior to the Volunteer movement is remarkably uneventful, but two episodes ruffled its political calm. They were the Wood's halfpence dispute of 1723–5, and the conflict between the Irish administration and parliament, 1753–6.

It was the extent and vehemence of the opposition experienced by the administration in 1723–5 that led to the evolution of the undertakers—powerful members of parliament who undertook to conduct government business through the house of commons in return for a share in the disposal of patronage.
Tendencies in Historical Study in England
Authors: Butterfield H.
Published: August 2016

In examining what seem to me to have been significant fields (or significant concentrations) of study in recent times, I wish to show how these have reacted on our conception of general history and how our very notion of the historian's universe has been undergoing a subtle transformation. In attempting to discuss some of the points where pressure has been exerted on historical study by war and international crisis, I wish to show how the very nature of history and the results of historical analysis prescrjbe to the historian his role when the momentous-ness of the contemporary world confronts him with claims and challenges. It will be useful to hold the figure of Lord Acton in the background, in order to measure the modern version of the human drama, and the modern view of the historian's function in the world, against the one which he so explicitly formulated.
The Government Forces Engaged at Castlebar in 1798
Authors: McAnally Henry
Published: August 2016

Statements as to the number of (and the elements composing) the government force which faced the French at Castlebar on Monday morning, 27 August 1798, differ widely and some of them are surprising. A history of the Irish rebellion published in 1898 by F. W. Palliser puts the number of the government troops at 16,000 or 17,000. Dr Richard Hayes gives the number as 5,000 infantry and 1,500 cavalry. Fortescue speaks of Lake arriving at Castlebar ‘ where Hutchinson had already assembled four thousand men chiefly militia and fencibles ‘, but he also speaks of his having been next morning at the time of the attack ‘ in a strong position with some 1,700 men ‘. The aggregate strength is by many writers stated as relatively ‘ more than thrice ‘ that of the French; a contemporary example of this is in the Annual Register for 1798.
State-aided Land Purchase under the Disestablishment Act of 1869
Authors: Shearman Hugh
Published: August 2016

It has been usual in works on nineteenth century Irish history to treat the Irish Church Act, 1869, as having been solely or predominantly an act of political justice and a setting right of an unfair relationship between churches and communities. The important place which the act holds in British economic policy as the first enactment for state-aided tenant purchase of land in Ireland has been generally ignored. What attention the subject of tenant purchase at that early period has received both from contemporaries and from subsequent writers has been mainly centred on the Landlord and Tenant (Ireland) Act, 1870, which was, in its tenant purchase provisions, a much less successful and less extensively applied measure. There are several reasons for this ignoring of the place of the Irish Church Act in the history of tenant purchase. Neither the act nor any part of it was classified as falling within the mass of legislation to which the collective citation of the Land Purchase (Ireland) Acts was given, nor was it specifically directed to be read as part of any of these later acts.
Concussion in Hockey: Compliance with Return to Play Advice and Follow-up Status
Authors: Ackery Alun , Provvidenza Christine , Tutor Charles H.
Published: August 2016

Objectives:

To determine the compliance rate among hockey players with concussion or other head injuries who were advised by a physician about return to play. To assess compliance of hockey players with return to play advice and to assess the incidence of long-term post-concussion symptoms.

Methods:

A retrospective chart review, telephone questionnaire and follow-up analysis of income, level of education and professional aspirations. The study examined 40 hockey players with concussion or other head injury treated at a neurosurgical ambulatory clinic, who had initial visits between 1995 and 2003, and had been seen at least two years prior to completing the questionnaire.

Results:

There was a 58% (23 of 40) participation rate in the study. Fifteen (65%) of the 23 participants were advised to never return to play, and 5 (33%) were non-compliant and returned to play. Four (80%) of the five non-compliant players continued to suffer from post concussion symptoms. Overall, 15 (65%) of the 23 players participating in the study continued to suffer post concussion symptoms at least two years after the clinic visit.

Conclusions:

Five (33%) of 15 hockey players advised to never return to play were non-compliant and returned to play, and four continued to suffer from post concussion symptoms two or more years later. After repeated concussions, 65% of hockey players had long-term sequelae that prevented return to play and produced long-term post-concussion symptoms.
The Use of Glass Cloth/Resin Moulded Components in the Laboratory
Authors: Irving F. G. , Saunders R. A.
Published: August 2016

The purpose of this note is to call attention to the convenience of glass cloth/polyester resin laminates as a means of constructing certain parts of experimental apparatus, such as small ducts or nozzles.

The advantages of the material are that it is strong, light in weight, easily worked in that heat and pressure are not required, and a high degree of accuracy and surface finish are easily achieved. For the purposes considered here, convenience in fabrication is the main consideration, since it is easier to shape the outside of a suitable male mould rather than the inside of a small duct.
Wind Tunnel Balance Design— The Simultaneous Measurement of Forces and Moments
Authors: Saunders C. G.
Published: August 2016

An electro-mechanical method of simultaneous component separation is suggested as an alternative to mechanical systems. Based on the commonly used weighbeam, employing a motor driven leadscrew, poise weight, selsyn repeater circuit and counter, component separation is proposed by means of the selsyn differential circuit.

The use of the selsyn motor as a direct or differential telemeter mechanism is well known, and as such, has many industrial applications. Such use, applied to the aerodynamic balance, offers the advantage of avoiding many of the difficulties associated with design and in particular, the construction of a mechanically independent and simultaneous measuring instrument.
Forty-First Wilbur Wright Memorial Lecture: Buckling and Stability
Authors: Hoff N. J.
Published: August 2016

Although columns built almost 5,000 years ago still stand in Egypt, the first theoretical calculation of the load-carrying capacity of columns was published by Euler only 209 years ago. The classical theory established in this publication is still the foundation of all stability analyses and is likely to remain so in the future. It was derived for perfectly elastic columns and for specific end conditions. These end conditions are not realised in the ordinary column test nor do they correspond exactly to the conditions prevailing in an aeroplane wing when it is subjected to a gust or to the shock of landing. They are not the same as the end conditions of a column in a building when it collapses during a tornado or an earthquake.
Foaming and Aeration of Oils in Aviation Powerplant
Authors: Tourret R.
Published: August 2016

The presence of foam or unduly aerated oil in the lubricating-oil systems of aircraft power plant can be very troublesome—more so in reciprocating engines than in gas turbines, since the rates of circulation are greater and the viscosity grade of the oil is higher. Consequently in this paper, which surveys present knowledge about oil foaming, reciprocating engines are the main consideration.

In the conventional aircraft “dry-sump” oil system, a simplified diagram of which is shown in Fig. 1, oil is pumped from a supply tank to the bearings, and so on, by a so-called “pressure” pump. This oil then drains down into the sump and is picked up by “scavenge” pumps which return it to the supply tank. There are usually at least two scavenge pumps so that the oil is cleared away irrespective of the attitude of the aircraft.
Measurement of Noise on the Ground from Aircraft in Flight
Authors: Fleming N.
Published: August 2016

In cases of noise nuisance, measurement of the noise has several uses. It helps in deciding the degree of noise reduction which is desirable; it may serve to identify the most important source or sources of the noise where this is in doubt; and it is of assistance in devising methods for reduction of the noise. For the first purpose a single figure to characterise the noise would be preferable, but for the others some form of noise analysis is needed.

To the sufferer from the noise the most important characteristic is the annoyance it causes, or its nuisance value. This may be assessed very differently by different individuals, and consequently it is not very amenable to measurement.
Minimising Zero-Drift in Electrical Strain Gauge Bridges
Authors: Urwin C. R. , Swainger K. H.
Published: August 2016

“Potential” leads are used to put strain gauge switches and leads in series with high resistance ratio arms in a modified Wheat-stone Bridge. Thus the effects of switch contact resistance change and temperature-resistance change in leads can be minimised to any desired values. The high resistance ratio arms allow coarse resistance changes at the measuring bridge to measure the small resistance change at the gauge due to strain.

High potentials are applied to the bridge to minimise the effects of thermal e.m.f.

Active gauges and the temperature compensating gauges are in circuit for only a few seconds while the measurement is made.
The Development of an Early Helicopter
Authors: Aldridge P. J.
Published: August 2016

It is only in very recent years that the helicopter has begun to find a place in the pattern of Aviation. Although its development has not been so intensive nor so widespread as that of the more conventional fixed wing aircraft it has remained a positive and progressive force running on a parallel course.

The idea of the screw, as a method of propulsion or lifting, is not new, yet at the beginning of the 20th century its use was still restricted to propelling ships. It is therefore not surprising to find that the development of an early helicopter was carried on in a shipyard.
The Pressure Rise with Subsonic Mach Number on Fuselages and Nacelles
Authors: Hartley D. E.
Published: August 2016

In treating the compressible subsonic flow by the Prandtl-Glauert method as extended by Göthert, the velocity increment v in the direction of the main stream is found to be 1/β2 times the corresponding velocity increment va on the analogous body in incompressible flow; the analogous body being obtained by reducing the lateral dimensions of the real body in the ratio β:1.
The Development of the Spill Flow Burner and its Control System for Gas Turbine Engines
Authors: Carey F. H.
Published: August 2016

Since the advent of the aircraft gas turbine engine, various ways have been employed for feeding the fuel into the combustion chambers in the most advantageous manner. Perhaps the most commonly employed method has been the use of swirl atomising nozzles, and in this group is the spill type which has been used successfully for many years in industrial oil burning furnace equipment.

Arising from the general review of burner nozzles made for the aircraft gas turbine engine in its early days, spill burners were used experimentally on the W2/700 engine. Among the problems encountered was that of achieving suitable flow matching characteristics between the several burners of a set and also, that of arranging a satisfactory control system. The knowledge gained by this early work has been made available and has proved helpful to those who chose to carry on with this particular type of fuel nozzle.
Recent Progress in Gliding
Authors: Yates A. H.
Published: August 2016

Gliding as a sport dates from the early nineteen twenties when German pilots, banned by the Treaty of Versailles from constructing or flying powered aircraft, turned their attention to constructing sailplanes. Their progress was remarkable and, after visits by some of their best pilots to England in 1929, many clubs were formed here together with an association of clubs, the British Gliding Association. Many of these clubs lasted only a few months but by 1937 a few were in a strong position and in November 1937 Squadron Leader (now Group Captain) Buxton gave a lecture to the Society reviewing developments up to that date. Developments in gliding are well recorded in the Journal of the B.G.A., Gliding, and in the other aeronautical periodicals, but it is proper that the Society should record periodically progress made in this branch of flying.
Recent Fog Investigations
Authors: Petterssen Sverre
Published: August 2016

Fog is the result of a condensation process near the earth's surface when the air is cooled below its dew-point temperature by one or more of the processes which will be discussed in the second part of this paper.

The classical experiments of Wilson (I) showed that some types of particles, now called nuclei of condensation, must be present in the air if condensation is to occur with a reasonable degree of supersaturation.
The Generalised Theorem of Three Moments for the Case of Parabolic Lateral Loading
Authors: Morris J.
Published: August 2016

In the usual Berry (I) expression of the generalised theorem of three moments (i.e., generalised in the sense that end load deflection effects are taken into account) the lateral loading on a continuous beam is regarded as uniformly distributed over each bay into which the beam length may be divided (either naturally by supports or artificially for convenience of analysis). In this paper the lateral loading is taken as distributed parabolically so that the resulting equations may be used as a sort of Simpson's rule for dealing with any arbitrary loading. By taking into account the “ sinking “ of supports any particular beam can be divided up into a convenient number of bays over each of which the lateral loading may be assumed to be parabolic. We may thus obtain reasonably accurate solutions for the bending moments, etc., in a continuous beam under almost any type of lateral loading.
A Theoretical Investigation of Plastic Torsion in an I-Beam
Authors: Christopherson D. G.
Published: August 2016

The distribution of stress in an I-beam in torsion is investigated by a method of successive approximation, and the regions of initial yielding are determined for several values of the angle of twist. Formulas are given for elaborating the methods of Southwell and of Shortley and Weller in order to facilitate this determination.

The value of the stress-concentration factor in the fillets is found to agree well with results obtained by soap-film tests, and regions of plastic flow approximate closely those observed by MacGregor and Hrones by the use of the etching method.
Propellers for High-Speed Aircraft
Authors: Gardiner G. C. I. , Brett P.
Published: August 2016

In presenting this paper an attempt has been made to examine the development of current propeller theory and practice to cover the range of aircraft speeds between 450 and 550 m.p.h., which at 36,000 ft. represents a flight Mach number range of about 0.68 to 0.83. Inevitably in such a discussion it has been necessary to peep over the wall into the realms of higher speeds, but no serious attempt has been made to cover such a controversial region because of the lack of experimental data.
Viscous Effects on Flattened Pitot Tubes at Low Speeds
Authors: Macmillan F. A.
Published: August 2016

Measurements were made of the pressures in flattened, blunt-nosed pitot tubes, in an air stream at Reynolds numbers from 13-1,000 (based on the external height of the tube). Three tubes were used, having cross sections with ratios of width to height (W/H) of 3, 7 and 11.
A Method of Rapidly Estimating Propeller Moment
Authors: Payne P. R.
Published: August 2016

In a Technical Note published in the April 1954 issue of the JOURNAL an approximate equation was presented for calculating the propeller moment of a helicopter rotor at the project stage, the solution to which could be obtained from two graphs.
The Boundary Layer and Recent Developments
Authors: Bairstow L.
Published: August 2016

As time passes more and more knowledge of the flow of fluids past bodies accumulates and of this increase some becomes applied to the problems of the day. Boundary layer theory is being applied at the present time to the problem of the degree of polish which should be given to a wing in order to reduce its profile drag to a minimum. Tests in the compressed air tunnel at the National Physical Laboratory and in flight at Cambridge and Farnborough have recently been directed to this point and give quantitative assurance of the correctness of theory. In what follows, a survey is made of a group of theorems relating to the resistance of various bodies such as aerofoils and flat plates and more generally to streamline forms. The theorems are partly physical and partly mathematical and approximations are numerous and of very different degrees of validity.
Study of Airscrews for High Speed Aeroplanes
Authors: Lazzarino Lucio
Published: August 2016

It is demonstrated how, with increase in speed, the diameter of optimum efficiency and the maximum possible value of efficiency of an airscrew diminish. The efficiency of a system of two counter-revolving airscrews with different angular velocities is then determined, and the variation of efficiency with variation in the relation between the angular velocities of the two airscrews.

With increase in the height and speed of flight, airscrew performance inevitably falls off, frequently in a marked degree; this being mainly due to the decrease in aerodynamic efficiency of the blade sections at high Mach numbers.

The object of the present article is to analyse the influence exerted upon the performance of an airscrew by the various parameters that determine it, wit-h special reference to those connected with the speed and height of flight.

A similar study has also been made of systems constituted of two counter-rotating airscrews, with a view to comparing them with isolated airscrews designed to absorb the same power under identical conditions.

By the methods here described, an approximate numerical evaluation of the performance can be made, utilising the experimental results which are already to hand.
The Stabilisation of a Thin Sheet by a Continuous Supporting Medium
Authors: Gough G. S. , Elam C. F. , Tipper G. H. , De Bruyne N. A.
Published: August 2016

The structural problems of metal aircraft design largely centre round the difficulty of making efficient compression members. This difficulty is accentuated when loads are small in relation to the size of the structure. For example, the diameter of an aeroplane fuselage cannot usually be less than the height of a man, which results in such small forces at the surface of the shell that the lightest practicable beam is quite disproportionate to its strength.

As a measure of load in relation to size, it is convenient to use a quantity that we suggest may be called the “ structure loading.” This quantity, due to H. Wagner (8), is simply the square root of the applied load divided by a characteristic dimension (such as the length) of the member.
New Research on the Use of Hardening Plastics for Aircraft Construction
Authors: Kuech Wilhelm
Published: August 2016

Laminated materials incorporating plastics seem to be especially well suited lor highly stressed aircraft components, by reason of their good strength properties. Paper, fabric and wood veneers treated with plastics on a phenolic basis were tested with regard to their strength, especially in bending, shear, absorbed energy in impact bending, notching strength and in their resistance against moisture. Further, the behaviour of compressed plastics was studied at different temperatures under static and dynamic loads. A part of the research was extended to pure phenol resin and to thermoplastics based on methacrylate and polyvinylchloride. The bonding properties of laminated compressed plastics were established. Concluding, some experiments relating to the practical manufacture of aeroplane components are communicated.
Stress Analysis of Thin Metal Construction
Authors: Cox H. L.
Published: August 2016

In seeking to analyse the stress distribution in a complex structure, our object is really twofold. In the first place, if the stress in each part is accurately known, the strength of each part separately can be assessed on the basis of tests on simple units and the necessity for testing the complete structure may be avoided. In the second place, if the stress distribution can be expressed as a function of the geometry of the structure, the effect of varying that geometry, particularly with the object of realising Holmes’ one-hoss-shay, can be examined theoretically and arbitrary-features of the design can be eliminated. If our knowledge were complete, any structure designed to a maximal or minimal condition would not permit any variation from one ideal form, the design would be uniquely determined by the stated requirements.
Some Modern Methods of Research in the Problems of Flight
Authors: Lewis George W.
Published: August 2016

As a guest of the Royal Aeronautical Society, I wish first to express my sincere appreciation of the opportunity to join those others who have appeared before you in years past to present the Wilbur Wright Memorial Lectures. To those of us who are primarily concerned with the scientific aspects of aviation this continuing series of lectures, now nearly as old as the art of human flight itself, is the finest tribute that could be offered in honour of the accomplishments of the Wright brothers. It is on this account that I feel most sincerely the honour and privilege that has been granted me through your invitation to present the Twenty-seventh Wilbur Wright Memorial Lecture.

The title—“ Some Modern Methods of Research in the Problems of Flight ”— is, I confess, somewhat ambiguous. At the time it was selected, some months ago, several investigations then in progress gave promise of results sufficientlyinteresting to be included.
Experimental Research in the Guidonia Supersonic Wind Tunnel
Authors: Ferri Antonio
Published: August 2016

Our first phase of activity, at the Guidonia supersonic wind tunnel, was devoted to studying and designing the necessary apparatus for carrying out systematic research. (See Captain Gasperi's paper, read before the Lilienthal Congress in 1937-) This apparatus consisted principally of:—

(1)

A series of transformer jets, to create the requisite speeds in the test chamber;

(2)

A balance, to determine the forces exercised by aerodynamic phenomena upon the objects under test;

(3)

The striometric and interferometric apparatus.

The initial study was long and laborious; since we lacked the great help furnished by previous research, which is nearly always forthcoming in similar studies, we had to proceed by means of successive experiments until the apparatus took its final shape. Eventually we evolved a series of jets, a balance and an optical installation which we hope are permanent. These, however, being still under construction, have not yet been tested.
The Fundamentals of Boundary Layer Theory, with Some Applications to Aircraft
Authors: Leaderman H.
Published: August 2016

The recently issued Report of the Aeronautical Research Committee draws attention to the fact that much work, apparently of academic interest only, is now of direct practical utility. In particular, the theories of the boundary layer and of turbulence, though admittedly very incomplete and uncertain and lacking a secure scientific foundation, have been developed to the stage in which they can be applied to explain and predict the behaviour of aircraft, and to show how aircraft may be improved. The physical structure of the boundary layer will be described, and the methods by which the problems have been attacked mathematically to get useful results and to check the theories.

In conclusion, the theory of the boundary layer will be applied to the calculation of the drag of an airship or aeroplane fuselage under full-scale conditions, and to an explanation of the behaviour and performance of different types of aerofoils.
The Domain of the Helicopter
Authors: Hafner Raoul
Published: August 2016

The Seventh Louis Bleriot Lecture was given in Paris on 10th March 1954, by Mr. Raoul Hafner, F.R.Ae.S., under the auspices of the Association Française des Ingenieurs et Tèchniciens de L'Aèronautique (A.F.I.T.A.)

The Lecture was attended by the President, Sir William S. Farren, C.B., M.B.E., F.R.S., F.R.Ae.S., and several members of Council of the Royal Aeronautical Society, by the Secretary, Dr. A. M. Ballantyne, T.D., A.F.R.Ae.S., members of the Society and of the British Aircraft Industry, and by a large and distinguished French audience.

Monsieur Jules Jarry, President of A.F.I.T.A., presided at the meeting and welcomed the guests before introducing Sir William Farren, President of the Society.
Empirical Formulae for the Determination of Stress Curves
Authors: Nicholls A. C.
Published: August 2016

In the analytical presentation of curves the main requirements perhaps are those of accuracy and simplicity and the problem confronting the engineer is the efficient combination of the two. A further important consideration is that of the range over which the empirical formula (or formulae in some cases) is to be effective, for clearly the greater this range is, the more useful will be the formula.

It is obviously desirable that any equation that is chosen should be as close a fit as possible to the practical curve. It must not be sensitive to small parametric differences and it should be possible to determine these parameters with a fair degree of precision.
The Use of Light Alloys in Aircraft Construction
Authors: Le Coeuvre R.
Published: August 2016

Light alloys now play a most important part in aircraft construction. It is probable that they will keep their present superiority over other materials which have been in use, because manufacturers are continually adapting light alloys to the need of the day.

Light alloys have, however, formidable rivals. There are many arguments for the use of wood, and we must recognise that in certain aspects (such as resistance to vibration and ease of working) the use of wood has definite advantages, particularly in the case of plywood.
The Stressing of a Tail Boom System for Fin and Rudder Side Loads
Authors: Morris J.
Published: August 2016

In certain types of aeroplane the empennage is carried on two tail booms emanating from the main body. In some cases the booms and tail plane form what is virtually a portal and in these circumstances a fairly simple approximation may be found for the stresses resulting from fin and rudder side loads. The method adopted follows the treatment given in the author’s paper, “The Stressing of Rigid Jointed Frames.”
Critical Speeds of Monoplanes
Authors: Hanson J.
Published: August 2016

The fact that attention must be given to stiffness as well as strength in aeroplane design is now generally recognised. The provision of adequate strength alone is not sufficient to ensure that an aeroplane is immune from such troubles as flutter, loss of lateral control due to twisting of the wing and wing divergence. This is illustrated by the case of the Puss Moth. As shown in R. and M. 1645 this machine was examined in detail by the Aeronautical Research Committee and found to be completely satisfactory as far as the existing official airworthiness requirements were concerned, and yet it experienced failures which were attributed to flutter, an instability involving the stiffness of the wings and tail.

In the earlier stages of the investigations into these stiffness problems it appeared to many practical people that the work. was of academic interest only. As a matter of fact it was of subsidiary importance while operational speeds of aeroplanes were relatively low, but the higher speeds of the modern aeroplane make such problems of direct practical interest.
Hydraulics for Aircraft
Authors: Bound R. H.
Published: August 2016

A meeting of the Society was held in the Lecture Hall of the Institution of Mechanical Engineers, Storey's Gate, St. James's Park, Westminster, London, S.W.I, on Thursday, March 22nd, 1945, at which a paper by Mr. R. H. Bound, F.R.Ae.S., F.S.E., M.I.M.E., A.M.I.A.E., on “Hydraulics for Aircraft,” was read and discussed. In the chair, the President, Sir Roy Fedden.
The Houston-Everest Flight
Authors: Fellowes P. F. M.
Published: August 2016

In this paper I propose not only to comment on the lessons learned in the flight over Everest and Kangchenjunga, but also to indicate approximately what is involved in the initiation and organisation of such an expedition. It can only be on the rarest of occasions that a scheme emerges full-fledged from the nests of the mind and this expedition was no exception.
Stalling
Authors: Melvill Jones B.
Published: August 2016

This is the fifth occasion on which I have had the honour to address our Society and the third time I have chosen to discuss the same subject: “The stalling of aeroplanes.” I should apologise for thus harping upon a single string were it not that no subject could be more appropriate to an address in memory of Wilbur Wright, and were it not that until the stall is thoroughly understood and its attendant dangers pushed out of the way, aviation will not be free to play the great rôle which it is undoubtedly destined to play in the civilisation of the world.
The Autogyro Rotor as a Sail
Authors: Moore-Brabazon J. T. C.
Published: August 2016

The idea of navigating a certain type of sailing boat of mine by an autogyro instead of an ordinary sail has long been a desire of mine, in that I always have considered sailors to be very out of date as to rigs.

In conversation with J. Weir this question arose, whereupon he said that he had within his organisation of the Autogyro Company an engineer named O. Reder who had the same desire. We, therefore, got in touch and although the time was very short got out a rig and installed it upon a very small onedesign class, well-known in the Solent, namely, the Redwing. These boats are about one ton, and the rules governing their racing are that the hulls are standard and that any rig can be used, but that the sail area must not exceed 200 sq. ft.
Research in the R.A.E. Tank
Authors: Coombes L. P.
Published: August 2016

Seaplane tank testing is an offshoot of ship tank testing, the technique of which was founded by William Froude nearly 70 years ago and is now highly developed. Apart from the fact that a scale model is towed through still water, however, there is little in common between the two systems of test, though one link remains in spite of dissentient voices; Froude's laws are used as the basis of correlation between model and full scale. In other respects, the conditions of operation of a ship and a seaplane on the water are so different that when the R.A.E. tank was built, the whole existing technique was reviewed.
Wind Tunnel Test of A R.A.F.28 Aerofoil with Thurston Rotors
Authors: Hartshorn A. S. , Callen C.
Published: August 2016

The suggestion has been put forward by Dr. A. P. Thurston that the characteristics of a wing can be considerably improved by adding self-starting rotors at or near the wing tips. It is claimed that by placing these on each wing near the leading edge improvements analogous to those of a slotted wing tip can be obtained together with slow landing characteristics. Previous experiments (1) have shown that rotors can give about the same degree of lateral stability as tip slots. The primary object of these experiments was to test the second assertion, and the criterion by which this should be judged was that the gliding angle should be as steep as possible for a given rate of descent.
Aircraft Production Methods
Authors: Gibson W. G.
Published: August 2016

The object of production is to give service to the user. The value of that service is generally measured by the results obtained (either by way of performance, ease of maintenance, reliability, long life, and appearance) against the cost; and given two similar products, by which I mean products designed to fulfil identical functions, the purchaser will prefer the one which gives him equivalent or greater service at the lesser cost.
Fuels for Aircraft Engines
Authors: Bass E. L.
Published: August 2016

It is unnecessary to enlarge on the importance of the fuels used in aviation in a paper before this Society. Not only is fuel quality the most important individual factor to be considered in the economics of civil aviation, but engine development, aircraft design and performance depend upon it.

An apology is offered, in view of the title of the paper, that as it is barely possible in the confines of a single paper to deal adequately with the volatile fuels (known as petrols and gasolines) used in the normal carburettor or homogeneous charge engines, other types of fuels have necessarily been omitted.
Cloud Formation and its Effect Upon Gliding
Authors: Walker Gilbert T.
Published: August 2016

The importance of healthy relations between the sporting and the scientific sides of gliding is very great; and the fact increases the responsibility of my task this evening as well as the honour that the Council of the Aeronautical Society have done me in asking me to undertake it. The history of gliding on the continent shows that at times when financial or other difficulties have given cause for anxiety, some development suggested on the scientific side has rekindled enthusiasm and given the movement a new vitality. Change is as essentially connected with a healthy sport as with a living organism. Nobody can visit the Wasserkuppe without being impressed by the zeal which prevails there; it is almost religious in its fervour, and although some of the neophytes of the hierarchy may be mere gymnasts fired with the team spirit, its bishops and its missionaries are inspired by their determination to advance knowledge.
Principles of Rocket Propulsion
Authors: Chatley Herbert
Published: August 2016

A great deal of interest has recently been taken in the subject of rocket propulsion, undoubtedly in the main due to the rather extravagant hopes, raised by Professor Goddard (I) in 1919, that a projectile might actually be sent into interplanetary space. Esnault-Pelterie (2) and Hermann Oberth (3) have more recently reaffirmed this possibility. Experiments by the late Max Valier, Reinhold Tilling, Darwin Lyon, Goddard himself and others have sustained the attention given to the matter. Prof. Richardson's article on jet propulsion (AERONAUTICAL JOURNAL, Jan., 1931) should be referred to. Mr. David Lasser's recent book (4) gives a fair general view of the subject, and the author's paper to the Society of Engineers (May 2nd, 1932) may also be of interest.
Winter Landing Gear
Authors: Ferrier A.
Published: August 2016

Snow falls in a great variety of forms, depending on a large number of conditions affecting the crystallisation of the moisture in the atmosphere. The forms may even vary from place to place or from time to time in one storm.

The character of snow as a medium for transportation depends not only on the form of its constituent crystals, but on the nature of the ground on which they fall, the depth of the total covering, the previous history of the underlying layers, and of course on the history of the last fall and the atmospheric temperature of the moment. Considering the characteristics for the purpose of aircraft operation, it is sufficient to make the broad classifications shown in Table I (page 504).
Engine Cowling with Special Reference to the Air-Cooled Engine
Authors: North J. D.
Published: August 2016

In the earliest stages of the development of the aeroplane the speed range obtainable was small, flight occurred only at fairly high lift coefficients, and induced drag was the predominant component of total resistance, hence successful flight depended on the achievement rather of minimum weight, minimum wing loading and maximum engine power than on the achievement of minimum possible parasite resistance.
A New Method for Calculating the Climbing speeds of Aeroplanes of Great Climbing Capacity
Authors: Otten G.
Published: August 2016

For the calculation of the climbing speeds of aeroplanes several methods are in use, which, as is well known, do not yield quite accurate results when applied to machines with great climbing capacities, and give rise to inaccuracies which become of greater importance with increasing climbing capacity of the plane. The climbing speed, up to the present, has not been great in respect to the forward speed used when climbing, so that for the calculation of the climbing speeds the method fairly generally used and described in the “Handbook of Instructions for Airplane Designers, ”from the U.S. Army Air Service, could be used without serious objections. It has, however, been found desirable to look for a better method for calculating the climbing speeds, owing to increasing engine powers accompanied by decreasing drag coefficients of the aeroplanes, as well as to the introduction of variable pitch airscrews.
The Refuelling of Aircraft in Fligh
Authors: Larrard J. H. B.
Published: August 2016

The establishment of contact between aircraft in flight for the purpose of refuelling, has until recently been regarded as a somewhat hazardous procedure employed mainly during attempts to create endurance records.

It would appear, however, that if such contact between aircraft could be established safely and as a routine operation, considerable advantages could be obtained by the employment of such a scheme.

From the point of view of commercial aviation, not only would it make possible long distance non-stop flights over regular air routes, but it would enable a large increase in pay load to be carried, since the bulk of the aircraft's consumable load, i.e., fuel, would not be taken on board until the aircraft had left the ground and climbed to a reasonable height.
Thirty Years of Theoretical and Experimental Research in Fluid Mechanics
Authors: Riabouchinsky Dimitri P.
Published: August 2016

In section 8 the author's apparatus for the study of skin friction, based on direct application of the momentum theorem, has been described (Fig. 99). In a paper published in 1914, this idea was further developed and it was shown that it is possible to calculate approximately in this way the skin friction and the distribution of air velocities in different régime.
Liquid-Cooled Engines-Design and Application to High-Speed and Other Aircraft
Authors: Graham Forsyth A.
Published: August 2016

The liquid-cooled engine is generally associated with high speed aircraft, and as I have had some experience in connection with the development of racing engines, when I received the honour of an invitation to read a paper for the Royal Aeronautical Society, I chose this title because it gave me a chance to further the cause of the liquid-cooled engine and to interest you in possible developments of engines suitable for high speed and other types of aircraft.

In attempting to forecast possible developments, I am taking a grave risk, as anything connected with aeronautical engineering is doubtful owing to the rapid changes which take place in a short time, and I can only indicate where I think improvements can take place, based on present progress, and can only hope that my remarks will invite criticism and discussion.

During the paper the “ hardy annual ” ‘ frontal area ’ will be raised; a slide will be shown of a liquid-cooled engine superimposed over an air-cooled radialof the same b.h.p.
The General Theory of Cylindrical and Conical Tubes Under Torsion and Bending Loads
Authors: Hadji-Argyris J. , Dunne P. C.
Published: August 2016

This paper presents a rational method of stressing single or many cell tubes particularly of the type encountered in wing structures. The theory has been developed for conical or cylindrical tubes of arbitrary cross-section the shape of which is maintained by a closely spaced system of diaphragms rigid in their own planes and parallel to the root section. Within the limits of the assumptions the theory is exact for right cylindrical tubes, and is applicable with adequate accuracy to cylindrical or conical tubes in which the inclination of any generator to the normal to the root plane does not exceed 10°.

The analysis given unifies the theories of bending and torsion and shows that the commonly used method of separating the bending and torsion loads by means of a shear centre is in general incorrect.

The formulae have been developed in such forms that attention is concentrated on the necessary corrections to the stresses as indicated by the ordinary engineers' theory. These correction terms include all effects of shear lag, diffusion, and end effects hitherto taken into account only in some very special cases.

Particularly important for practical applications is the structure consisting of a number of direct stress carrying members (booms) connected by walls effective only in shear. The simplest structure of the latter type is the four-boom tube with or without nose and trailing cells, and in this case explicit formulae are given which are immediately applicable to practical calculations. Formulae are also given for the more complex case of a six-boom tube in which the two extra booms are introduced to represent more accurately the direct stress carrying capacity of the top and bottom panels between the two spars.
An Automatic Variable Pitch Airscrew
Authors: Townend H. C. H.
Published: August 2016

Some wind tunnel experiments have been made on a variable pitch airscrew which shall change its pitch automatically as V/nD changes. The change in pitch is operated by the resultant effect of centrifugal and aerodynamic forces.

Reduction in air density, e.g., due to increase in height, causes an increase in pitch.

In the event of engine failure the blades assume the position of minimum drag.

A tentative design for a model screw, together with tests thereon, are described, and it appears that if the friction in the bearings about which the change in pitch occurs can be made reasonably small, it should be possible to construct a satisfactory full-scale screw.
Thurston Wing - Tip Rotors Control Beyond the Stall
Authors: Thurston A. P.
Published: August 2016

Three great drawbacks of modern aeroplanes, from a safety point of view, are their tendency to stall, their high landing speed, and their low gliding angle.

The use of wing-tip slots for preventing lateral instability is well known, but they do not materially reduce the landing speed. Moreover, they cannot be used along the whole span without making the wing unstable. The best length of wing-tip slot for securing stability and maintaining the lift coefficient is about 40 per cent, of the semi-span.
The Development, Design and Construction of Gliders and Sailplanes
Authors: Lippisch A.
Published: August 2016

The Gliding and Soaring Flight movement is as old as History. The observation of bird flight must have shown the men of former centuries in the same way as our own generation, that apart from power flight with wing beats there must be another flight possibility, enabling the use of the energy in the movement of air masses for flight without the expenditure of other power. The experiments undertaken in these times on the solution of the flight problem have come down to us only through myths and sagas, and we cannot differentiate between truth and imagination in these stories.

Experimental research, which can certainly be considered as the foundation of modern physics, has also in the realm of aerodynamics laid the basis for modernaeronautics. In this gliding and soaring flight plays the rôle of full–scale experiments, not as an end in itself, but as a proving-ground and last station before the invention of power flight.
The Lift Distribution on a Twisted Elliptic Wing, with Special Reference to the Effect of Flaps
Authors: Lockwood Taylor J.
Published: August 2016

Problems involving discontinuous aerodynamic twist, as for a flapped wing, are not readily soluble for wings having a rectangular plan form or straight taper. Lotz's method (B.Ae.S. Journal, May, 1934) has been stated to be particularly suitable, but a recent American report used in preference a direct method of successive approximation. In either case a fair amount of labour is involved, and the final results are only approximate. The exact solution for a wing of elliptic plan form, whilst no-t directly applicable to the usual type of tapered monoplane wing, is readily obtainable, and should give a good idea of the lift distribution and induced drag due to a flap on an actual wing.
Ten Years' Gliding and Soaring in Germany
Authors: Georgii Walter
Published: August 2016

Before passing to the subject of the paper may I ask your indulgence for my limited knowledge of English, which prevents my giving a free discourse, and constrains me to a set lecture. This I view with regret since it makes it difficult to impart to my words the lively and vivid feeling which a more formal picture of the importance and attractiveness of gliding flight may not give.

We are looking back on ten years of development and on an unbroken series of ten gliding competitions held at the Wasserkuppe in the Rhön, since 1920.
The Stressing of Rigid-Jointed Frames
Authors: Morris J.
Published: August 2016

The investigation of the strength of a rigid-jointed frame is a problem of considerable practical importance. The precise effects of the secondary stresses arising from the rigidity of the joints have in the last half century been the subject of much speculation. But the calculation of these secondary stresses is extremely tedious by any existing method and in consequence they have rarely been ascertained with any degree of accuracy. The first real attack on the problem was made by Manderla in his Munich Polytechnic prize essay–“ The Calculation of Secondary Stresses which Occur in Simple Trusses ”–published in 1880 in Allgenieine Bautzeitung.
Airscrew Development
Authors: Watts H. C.
Published: August 2016

Airscrew development has proceeded along four main lines :–

(1)

Aerodynamic design.

(2)

Materials.

(3)

Adaptation to engine and aircraft.

(4)

Fans for cooling and ventilating purposes.

Section (4) I have omitted. It may form the subject of a paper elsewhere. Section (1) I have barely outlined. It is of great interest, but I have concentrated on Sections (2) and (3) as being of immediate practical concern.
Comfort in Air Travel
Authors: Zand Stephen J.
Published: August 2016

When the Royal Aeronautical Society did me the honour several weeks ago of asking me to give a lecture on sound-proofing of aircraft, I hoped to be able to prepare a formal paper and read it to you. I did not realise at that time, however, that my temporary duties as consulting engineer to the civil aircraft division of the French Air Ministry would take practically all my time. So I arrived in London with only the scantiest notes and shall be obliged to talk more or less extemporaneously on the broader subject of comfort in air travel. I hope that I may have the opportunity to supplement this lecture by a more elaborate paper at a later time.
The Part Played by Skin-Friction in Aeronautics
Authors: Lanchester F. W.
Published: August 2016

The early work of Froude. Relation of skin-friction to resistance arising from other causes. The Langley fallacy. The Reynolds Number and the condition of laminar flow: expressed graphically. Resistance as a functionl of velocity. Ichthyoid or streamline bodies: exemplifield in the Graf Zeppelin airship, etc.