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- Publisher
- Emerald Publishing
- Copyright
- Copyright © Emerald Group Publishing Limited
- ISSN
- 0002-2667
- DOI
- 10.1108/eb032578
- Publisher site
- See Article on Publisher Site
Abstract
cussed in the light of the latest available know ledge. Consideration is given to the stress pattern Fifth Anglo-American and to the various loading conditions to which a cabin is subjected. Fatigue testing of a com plete fuselage in water is discussed and some of the latest R.A.E. equipment described. Aeronautical Conference Some Influences of Equipment Installations and Brief Summaries of Papers Presented at the Conference of the Systems on Aircraft Design: C. F. Joy. (Handley Page Limited.) Institute of the Aeronautical Sciences and the Royal Aeronautical Society The paper outlines some of the more important Held at Los Angeles, June 20—23, 1955 influences of equipment installations and systems on the aerodynamic and structural design of air craft, primarily large high-speed subsonic aircraft. Operation of Turboprop Aircraft: P . G. Masefield. with theory. Certain effects of shock-induced (British European Airways.) boundary-layer separation on the flow past aero Power Control Systems for Aircraft: J . W. Ludwig. foils at transonic speeds are examined. This paper covers British European Airways' (Chance Vought Aircraft, Inc.) experience with the operation of turboprop air Contributions to Fluid Mechanics from Shock Tube The need for a controls design concept is craft and concludes with some thoughts on their Research: G. N . Patterson and I. I. Glass. (Insti stressed. Methods for improving servo character future possibilities. tute of Aerophysics, University of Toronto.) istics are described, and the need for an adequate reliability programme is described. Air-Line Use of Elementary Statistical Methods The idealized theory of the shock tube and in Aircraft Performance Measurement: W. C. observed deviations are described. The macro Mentzer and F . S . Nowlan. (United Air Lines, Inc.) scopic properties of gas flows at high Mach num Je t Noise: F . B . Greatrex. (Installation Division, bers are discussed from the molecular point of Rolls-Royce Limited.) The paper outlines fundamental differences be view. tween manufacturers and operators in so far as The paper describes noise tests on various their interest in performance data and their ability engines and on various noise reduction devices, Hypersonic Flow: L . Lees. (California Institute of to obtain such data are concerned. It then dis successful and unsuccessful. The application of Technology.) cusses briefly certain statistical principles and il these devices in practice is discussed. lustrates the use of these principles in the analysis This paper discusses some of the areas in which of performance data gathered by an air line. our understanding of hypersonic flows has pro Combustion for Aircraft Engines: W. T. Olson. gressed in recent years. Particular emphasis is (Fuels and Combustion Research Division, Design of High-Speed Aircraft: E. H. Heinemann. placed on hypersonic similarity and the hyper National Advisory Committee for Aeronautics.) (El Segundo Division, Douglas Aircraft Com sonic approximations; the interaction between the boundary layer over a slender body and the The paper will discuss combustor requirements pany, Inc.) 'external' inviseid flow; and the flow over blunt for turbo-jet and ram-jet engines. Each of the The author reviews some of the principal bodies, including the heat transfer problem. The basic processes that take place in combustors will obstacles and problems encountered in recent outstanding problems and the directions of some be examined. These include atomization and high-speed aircraft designs, some of the limita of the current research in this field are indicated evaporation of fuel, mixing, ignition, flame pro tions of the future, and the principal character in the course of the discussion. pagation, and flame quenching. The influence of istics of some of the recent aeroplanes developed fuel type and combustor design on performance under his supervision. will be discussed. On the Behaviour of Boundary Layers a t Supersonic Speeds: R. J . Monaghan. (Aerodynamics, Royal Design of Large Helicopters: B . Kelley. (Bell Air Aircraft Establishment.) craft Corporation, Texas Division.) Low-Consumption Turbine Engines: A. A. Lom A discussion of the behaviour of boundary bard. (Aero Division, Rolls-Royce Limited.) The paper reviews fifteen years of rotor design, layers at supersonic speeds, with particular refer discusses optimum size and configuration, and The relative importance of specific fuel con ence to the practical implications concerning drag uses a general approach suitable for members of sumption and specific weight are discussed, to and aerodynamic heating. The speed range that the aviation industry who are not familiar with gether with a comparison of the performance of is covered is up to about Mach 10. technical details of the helicopter. the pure jet , the by-pass, and the propeller turbine. Some Results of the Princeton University Smoke Stress Analysis of Multiweb Boxes: W. S. Hemp. The Variable Stator Jet Engine: C. J . Walker, Flow Visualization Programme: D. C. Hazen. (The College of Aeronautics.) and G. Neumann. (A.G.T. Division, General (Department of Aeronautical Engineering, Prince Development of theoretical analysis for the Electric Company.) ton University.) stress distribution in multispar swept wings and This paper describes the development of single This paper is a commentary to a 40-min. film derivation of detailed formulae for the nonswept rotor high pressure ratio compressors, using the showing typical results of smoke flow tests of two- case and comparison with experimental results of variable stator principle, and their application to dimensional and three-dimensional flow fields a nonswept specimen are presented. jet engines. utilizing the photographic and testing techniques developed at Princeton during the past three The Interaction Between Shock Waves and Bound years. ary Layers: D. W. Holder. (National Physical Power Plants for Supersonic Flight: E. S. Moult. (The De Havilland Engine Company, Ltd.) Laboratory.) Fatigue of Pressure Cabins: P . B. Walker. (Struc The paper discusses experiments on the inter The paper reviews possible types of power plant tures Department, Royal Aircraft Establishment.) action between shock waves and boundary required to propel aircraft at speeds equivalent layers and, where possible, compares the results The problem of pressure cabin fatigue is dis to Mach 2 o r Mach 3 in the stratosphere. A. 109 and A. 110 and A. 112:1954. It is considered that the simple selection of six fits BRITISH STANDARDS given in sheet 1 will meet the needs of a large propor A.109 and A.110. Shear bolts and nuts (Unified tion of the requirements of normal engineering pro hexagons and UNF. threads) for aircraft. Copies of the following Specifications may be obtained ducts. Price 5s. from the BRITISH STANDARDS INSTITUTION, The five fits given in data sheet number 2 supple A. 112. Cadmium plated shear bolts (Unified Sales Department, 2 Park Street, London, W.1, at ment the primary selection and it is thought that the hexagons and UNF. threads) for aircraft. the prices indicated. two sheets will, between them, cover about 95 per cent Price 3s. of the fits used in average good quality engineering. These British Standards specify the materials, S.P. 113:1954.—Cadmium Plated Close Tolerance Price 1s. each (12 copies or more 6d. each.) dimensions, finish and testing of shear bolts and nuts Shear Pins for Aircraft. B.S. 1054:1954.—Engineers' Comparators for External for use on aircraft and contain details of the method This British Standard specifies the materials, dimen of identification. A.112 provides a range of steel bolts Measurement. sions, finish and part numbers of the shear pins, which cadmium plated to be suitable for insertion in alu Many advances in the design of measuring instru are cadmium plated to be suitable for insertion in minium alloy materials. ments have been made since the British Standards aluminium alloy material. The standard is divided Institution first published B.S. 1054 in 1942, and com B.S. 1916 and 1916D:1954.—Data Sheets for Limits into three sections, the first specifying the require parators are now made with magnification factors of and Fits. ments applicable to all pins, and the others dealing 10,000 and over. The standard has, accordingly, been with the particular requirements for pins machined Following on the publication of B.S. 1916, Parts 1 revised to include provisions for these more sensitive and 2, the British Standards Institution now present from bar and those produced by a cold heading instruments and the opportunity has also been taken data sheets giving primary and secondary selections process. to clarify certain of the general requirements. of fits extracted from the main standard. Price 3s. Price 2s. 6d. Aircraft Engineering
Journal
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Jul 1, 1955