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Article
Publication date: 1 May 1956

D.B. Spalding

Typical performance data for combustion chambers with separate introduction of fuel and air have already been presented in FIG. 1. Comparison with FIG. 7, typical of one‐stream…

47

Abstract

Typical performance data for combustion chambers with separate introduction of fuel and air have already been presented in FIG. 1. Comparison with FIG. 7, typical of one‐stream chambers, reveals some important differences. Firstly, the data are neither confined within the inflammability limits nor have their peak at the stoichiometric O.F.A.R.; the shift is usually towards the weak side. Secondly, the ratio of the maximum O.F.A.R. to minimum O.F.A.R. of a given curve may be many times the corresponding range of a one‐stream chamber. Thirdly, the curves do not all terminate at substantially the same value of combustion efficiency. Particularly the second of these features is of great practical importance, for, in gas turbines, combustion chambers are required to cope with a very wide range of O.F.A.R. and must maintain a high efficiency throughout this range. The possibility of designing for a wide O.F.A.R. range is one of the reasons for using a two‐stream in preference to a one‐stream chamber. Some of the design features influencing O.F.A.R. range will be discussed below.

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Aircraft Engineering and Aerospace Technology, vol. 28 no. 5
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 March 1956

S.L. Bragg

THE second Combustion Colloquium organized by the A.G.A.R.D. (Advisory Group on Aeronautical Research and Development to the N.A.T.O. Countries) was held at the University of…

54

Abstract

THE second Combustion Colloquium organized by the A.G.A.R.D. (Advisory Group on Aeronautical Research and Development to the N.A.T.O. Countries) was held at the University of Liege, in Belgium, on December 5–9 last, and was attended by about 200 delegates. The seventeen papers which were presented and discussed were grouped under the following headings, although their subject matter sometimes overlapped these boundaries:

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Aircraft Engineering and Aerospace Technology, vol. 28 no. 3
Type: Research Article
ISSN: 0002-2667

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Publication date: 16 September 2024

Hamide Elif Üzümcü

This chapter draws on an ethnographic study with children aged 10–14 and their parents from heterogeneous socio-economic backgrounds in Türkiye. Building on a relational approach…

Abstract

This chapter draws on an ethnographic study with children aged 10–14 and their parents from heterogeneous socio-economic backgrounds in Türkiye. Building on a relational approach, it employs parental surveillance and children's individual privacy management in their intrafamilial relationships as a point of entry to reflect on childhood masculinities. From the perspectives of boys, girls and their parents, it illustrates how children's experiences of achieving privacy emerge as a gendered and age-related cultural phenomenon. Looking particularly at family negotiations around personal spaces and time at home and outside, it suggests that privacy regulation is a significant aspect of everyday family lives through which childhood masculinities and femininities are constructed, reproduced and performed. It further argues the ways that Turkish parenting culture may view intergenerational dialogue as a hierarchic category, rather than a relational category, contribute to a generational divide in boys' and girls' access to individual privacy.

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Article
Publication date: 1 October 1962

This book contains the proceedings of the third U.S.A.F. Office of Scientific Research Astronautics symposium and, consequently, suffers from not being a coherent whole but a…

20

Abstract

This book contains the proceedings of the third U.S.A.F. Office of Scientific Research Astronautics symposium and, consequently, suffers from not being a coherent whole but a scries of different papers; some of them, indeed, being ‘vistas’ but often leaving gaps in subject matter. It is a pity that some of the authors cannot be persuaded to write a conventional book on the subject, whereby these gaps could be filled.

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Aircraft Engineering and Aerospace Technology, vol. 34 no. 10
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 March 1969

Mr P. W. Lomax, B.Sc.(Econ.), has joined the Hoffmann Manufacturing Co. Ltd. as Market Research Manager, a new appointment within the organisation. Mr Lomax is responsible to Mr…

20

Abstract

Mr P. W. Lomax, B.Sc.(Econ.), has joined the Hoffmann Manufacturing Co. Ltd. as Market Research Manager, a new appointment within the organisation. Mr Lomax is responsible to Mr G. E. Saunders, Director and Administrative Manager of Hoffmann.

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Aircraft Engineering and Aerospace Technology, vol. 41 no. 3
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 April 1956

D.B. Spalding

The paper is mainly concerned with how the gas‐turbine designer can choose the best design of liquid or gaseous fuel combustion chamber for his purpose. In the method proposed…

136

Abstract

The paper is mainly concerned with how the gas‐turbine designer can choose the best design of liquid or gaseous fuel combustion chamber for his purpose. In the method proposed, combustion chamber test data are expressed in a way which gives the most general information about the design, by introducing dimensionless performance criteria. These criteria are then plotted in ways which enable the various chamber designs to be compared. The treatment deals implicitly with the conditions which satisfactory model tests must fulfil. An idealized model of a gas‐turbine combustion chamber is introduced in the light of which the effects of changes in overall fuel/air ratio can be explained more satisfactorily than when conditions in the flame‐tube are supposed homogeneous.

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Aircraft Engineering and Aerospace Technology, vol. 28 no. 4
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 June 1960

H.L. Price

An examination is made of the way in which the ground resonance properties of a helicopter depend on the fuselage damping, blade damping, drag hinge offset, inter‐blade spring…

46

Abstract

An examination is made of the way in which the ground resonance properties of a helicopter depend on the fuselage damping, blade damping, drag hinge offset, inter‐blade spring stiffness, blade mass and angular velocity of the rotor as specified by the parameters λƒ, λβ, Λ1, Λ2, Λ3 and Ω respectively. A direct method of drawing stability boundaries in the (Ω, λβ) plane is developed, and the geometry of these boundaries as the remaining parameters vary is studied theoretically at length. Arising out of the geometry, the validity of Coleman's criterion for stability is examined, and it is shown that the requirement that the product λƒ,λβ should have a certain minimum value is not itself sufficient to ensure stability for all Ω. The condition can be made sufficient by a proper and unique choice of the individual values of ?f and ??, and these values are found in terms of Λ1, Λ2, and Λ3. All other cases of stability require a larger value of the product λƒ, λβ. An alternative criterion for stability is developed which gives the minimum value of λƒ capable of ensuring stability for all Ω. This, and the preceding criterion, are mathematically exact, and follow from Coleman's equations of motion as applied to the case of a helicopter on isotropic supports. A brief account is also given of the case of a rotor having inter‐blade friction damping as against the viscous damping previously assumed.

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Aircraft Engineering and Aerospace Technology, vol. 32 no. 6
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 June 1950

J.S. Glass and J. Kestin

WHEN evaluating engine efficiencies, mean effective pressures or the work done by the piston in internal combustion engines or compressors, it is generally assumed that the state…

62

Abstract

WHEN evaluating engine efficiencies, mean effective pressures or the work done by the piston in internal combustion engines or compressors, it is generally assumed that the state of the working fluid is uniform throughout its mass. From this it follows that the expression for work where P denotes pressure and V, volume, holds. Now, it is known that, strictly speaking, this expression applies only in the limiting case of zero piston velocity, when the motion of the piston, and the thermodynamic process in the cylinder are said to be quasi‐static. The question, therefore, poses itself as to how far such an assumption is justified, when applied to a modern high‐speed reciprocating engine, say, an aircraft or motorcar engine, when piston velocities of the order of 40 ft./sec. are encountered.

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Aircraft Engineering and Aerospace Technology, vol. 22 no. 6
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 October 1963

I.M. Hall

THE development of undergraduate teaching in Aeronautical Engineering at Manchester University has followed a different pattern from that in most other Universities in this…

112

Abstract

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

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Aircraft Engineering and Aerospace Technology, vol. 35 no. 10
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 July 1962

This book is a paperback republication of the original edition published in 1950. (Reviewed in Aircraft Engineering, Vol. 22, p. 243). It opens with a section on Fundamental…

24

Abstract

This book is a paperback republication of the original edition published in 1950. (Reviewed in Aircraft Engineering, Vol. 22, p. 243). It opens with a section on Fundamental Theory which covers the main thermodynamic principles and kinematics of motion. The mathematical derivations of divergence and circulation are then discussed. The potential equation is introduced, and the solutions of its linearized form are described for two dimensional and axisymmetrical flows. The theory of characteristics is deduced and applied to plane and axisymmetrical cases. The basic normal and oblique shock relationships are first established for plane flows with emphasis on the shock polar and are then extended to the case of the cone at zero incidence. The hodograph transformation is outlined without particular application.

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Aircraft Engineering and Aerospace Technology, vol. 34 no. 7
Type: Research Article
ISSN: 0002-2667

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