School of Engineering (SoE)
Permanent URI for this community
Browse
Browsing School of Engineering (SoE) by Type "Report"
Now showing 1 - 20 of 561
Results Per Page
Sort Options
Item Open Access 1966 international toy fair Nuremberg 13 - 18 February(College of Aeronautics, 1966-02) Smith, Charles E.Nuremberg is a magic city. For one week each February this quaint but bustling place becomes an international wonderland. Not only is a fortune in toy business transacted but a very warm and human thing takes place. Visitors renew old associations and make new ones. Germans, Amercians, Britons, Poles, Belgians, French, Italians, Czechs, Swedes, Danes, Russians, Orientals, and others are involved in the largest display of toys in the world; and with each other, Peoples attitudes toward merchandise become stereotyped after a number of years in the toy business. But their attitudes and behavior toward their one time a year friends take on a new vitality each succeeding year. For American toy buyers the Nuremberg Spielwarenmesse (Toy Fair) offers a convenience of shopping not found elsewhere. The slick, high pressure salesmanship of New York is absent here. It is truly a buyers market. For the American toy manufacturer, Nuremberg affords 4 he opportunity to broaden his market and sources of supply as well as the chance to look for hew items, and even more important, new ideas. The exhibitions are held in five connecting buildings and there is an ample sprinkling of restaurants, snack bars, and vendors purveying the popular Nuremberg bratwurst. These are small sausages served with or without sauer- kraut and mustard. The buildings are well lit and well heated. This year these pleasant physical conditions were supplemented by unseasonably warm, clear weather.Item Open Access 2-port as an anlalogue of the Lorentz transformation of special relativity theory(College of Aeronautics, 1961-04) Deards, S. R.If the variables associated with a linear resistance 2-port are identified with the variables of special relativity theory, it is shown that a resistance 2-port transforms its port variables according to the Lorentz equations.Item Open Access Ablation studies of low melting point bodies in a pre-heated supersonic air stream(College of Aeronautics, 1960-02) Cleaver, J. W.This report is an investigation into the melting of axi-symmetric and two-dimensional bogies at a Mach No. of M[infinity] = 1.78 and stagnation temperatures up to 550 [degrees]K. In this temperature range, the most suitable material for the models was found to be an eutectic tin-lead alloy a melting point of 456 [degrees]K. For the cone and hemisphere-cone models two distinct modes of melting were observed. In cases where the estimated equilibrium surface temperature (Tw)o was approximately equal to the material melting temperature Tm, melting occurred only at the stagnation point of the model and was such that a flat surface normal to the gas stream always resulted. If the average rate of heat transfer at the air-liquid interface be defined as qi = LmPm x, where Lm is the latent heat of fusion, Pm is the density of the material and x is the rate of recession of the flat surface, it is found that qi decreases with increase of the radius of the flat nose. A very approximate theory is found to show some agreement with the experimental rates of heat transfer. When (Tw)o was considerably greater than Tm the flat surface was no longer preserved and the resulting steady ablating shape was paraboloidal in nature. When this occurred x was usually constant. This allowed some average steady state heat transfer rates to be evaluated and compared with theory. Preliminary tests were also made with a two-dimensional wedge model.Item Open Access An abstract of a paper by D. Battat 'a new kinetic approach to the shock wave structure'(College of Aeronautics, 1966)Item Open Access The acquisition of high speed skills. First progress report on D.S.I.R. research project(College of Aeronautics, 1963-04) Whitfield, D.N/AItem Open Access Addendum to a theoretical and experimental study of the boundary layer flow on a 45 degrees swept back wing(College of Aeronautics, Cranfield, 1957-11) Walton, J.COA report 109 describes Flight Tests carried out on a swept back half wing of double elliptical section to investigate the nature of the boundary layer flow, with particular reference to Bounday Layer Instability and subsequent transition.Item Open Access Addendum to type record. Avro "Lancaster" Mk.1 P. A. 474 Type record No. 1/P1/Lancaster. Investigation of boundary layer conditions on wings. M.O.S. Contract No.6/Aircraft/9807/C. B. 6(a)(College of Aeronautics, 1956-01) College of Aeronautics, Department of Aircraft DesignIntroduction The investigation involves, briefly, the mounting of a wing of 45' sweep-back in a dorsal position on the fuselage of 'Lancaster' P.A.474 such that wing incidence will be variable in flight over a 20 range, i.e. ± 100. A ‘partial chord’ technique for swept wings has been established by the College using a similar wing mounting configuration on an Avro 'Anson' Aircraft and this technique has been applied to the current investigation.Item Open Access An advanced course in air transport engineering(College of Aeronautics, 1966-08) Hyde, DavidIn 1963 K.G. Wilkinson, then Assistant Chief Engineer of British European Airways, emphasised the lack of formal engineering education in the maintenance and operation of aircraft. This report describes the nine-month postgraduate-level course in Air Transport Engineering which was started in October, 1964 at The College of Aeronautics, Cranfield, in order to help in satisfying this requirement.Item Open Access The aerodynamic characteristics of a family of related hovercraft shapes(College of Aeronautics, 1967-09) Andrews, E. J.The handling qualities of hovercraft indicate the need for a better understanding of the influence of the basic aerodynamic characteristics. This report is the first of a series in which the aerodynamic characteristics of hovercraft shapes are studied with particular reference to current design variables starting with simple solid block models and progressing to more sophisticated hollow models having cushion efflux and air-induction.Item Open Access Aerodynamic characteristics of a swept wing with spanwise blowing.(Cranfield University, 1956-09) Ayers, R. F.; Wilde, M. R.This report is the first of a series of studies to investigate the effectiveness of a spanwise blowing on the aerodynamic characteristics of low aspect ratio wings and bodies. The model used in this investigation was an untapered half-wing aspect ratio 1.39,50 degree sweep back, and mounted on a reflective plate.Item Open Access The aerodynamic characteristics of the jet wing and its application to high speed aircraft(College of Aeronautics, 1961) Alexander, A. J.The slender wings and bodies suitable for supersonic flight have, in general, relatively poor aerodynamic characteristics especially at lay speeds. In order to improve their performance the use of edge blowing has been explored. In this scheme high velocity air jets in the form of thin sheets are used to fix separation lines on the wing or body and to favourably influence the external stream. Thus the equivalent wing, called here the "Jet Wing” is composed of the wing-body itself plus the extended curved jet sheets which spring from its edges. A limited use of edge jets has been proposed in the 'Jet Flap' concept but the efficiency of this device fails off with decreasing aspect-ratio and the problem of trimming could be severe as most of the increased lift is generated near the trailing edge. At very law aspect-ratios a considerable part of the lift is contributed by the leading-edge vortices which dominate the flow field at moderate incidence. It follows therefore that leading edge blowing is particularly useful for small aspect-ratio wings and the trimming problem can be avoided by a suitable jet arrangement which does not disturb the conical nature of the flow. When sufficiently large auxiliary thrusts are available peripheral jet sheets can be deflected downwards close to the ground, the air craft becoming a Ground-Effect-Machine, with substantial reductions in both take-off and landing speeds and distances.Item Open Access Aerodynamic characteristics of two low aspect ratio rectangular wings at Mach 2(College of Aeronautics, 1956-04) Marson, G. B.This note summarises the important results of a detailed experimental investigation into the flow and pressure distribution over two rectangular single wedge wings. The experiments were carried out .in the 9" x 9" supersonic tunnel at the College of Aeronautics, 6 at a Mach number of 2.0 and a Reynolds number of 2.5 x 10 per foot. Both wings had a chord of 3 inches and a total wedge angle of 6°. They had no real trailing edge, but were faired into a cylindrical support which could be rolled and pitched in the tunnel. Wing A was of 2 inch1span, giving an aspect ratio of 0.67. `Ting B was of 1 1/4 inch span, 0.42 aspect ratio. 132 pressure tappings 4 were spaced regularly over half of one surface of each wing, and up to 19 pressure readings could be taken simultaneously on vertical mercury manometers. models were pressure plotted at pitch angles of 0°, 2 1/2°, 5°, 7 1/2°, 10°, 15°, 20°, 25°, and 30°, and at all roll angles at intervals of 30°. Since each wing was symmetrical about the centreline, the complete pressure distribution over all surfaces at any roll angle Ø could he obtained from the readings taken on the one surface at Ø, 180°- Ø, 180° + Ø, and 360°- Ø. The pressure readings were then integrated to give the forces and moments on the complete wing… [cont.].Item Open Access The aerodynamic derivatives of an aerofoil oscillating in an infinite staggered cascade(College of Aeronautics, 1960-01) Craven, A. H.Thin aerofoil theory is used to obtain, in integral form the aerodynamic derivatives of an aerofoil oscillating in an infinite cascade. The theory allows for arbitrary stagger angle and phase difference between adjacent blades of the cascade. The expressions obtained reduce, for zero stagger and for in phase and antiphase oscillations, to known results.Item Open Access The aerodynamic derivatives with respect to rate of yaw for a delta wing with small dihedral at supersonic speeds(College of Aeronautics, Cranfield, 1949-03) Hunter-Tod, J. H.Expressions are derives for the yawing derivatives on the assumptions of the linearised theory of flow for a delta wing with small dihedral flying at supersonic speeds at small incidences. The non-dimensional derivatives are numerically decreasing functions of Mach number. The non-dimensional rolling and yawing derivatives are also numerically decreasing functions of aspect ratio. When the wing lies entirely within the apex Mach cone there is a leading edge suction force proportional to incidence which makes a destabilising contribution to the yawing moment and side force which may be of the same magnitude as that from the inducted excess pressure distribution.Item Open Access The aerodynamic derivatives with respect to sideslip for a delta wing with small dihedral at supersonic speeds(College of Aeronautics, 1947-12) Robinson, A.; Hunter-Tod, J. H.Expressions are derived for the sideslip derivatives on the assumptions of the linearised theory of flow for a delta wing with small dihedral flying at supersonic speeds. A discussion is included in the appendix on the relation between two methods that have been evolved for the treatment of aerodynamic force problems of the delta wing lying within its apex Mach cone. Continues…Item Open Access Aerofoil theory for swallow tail wings of small aspect ratio(College of Aeronautics, Cranfield., 1950-10) Robinson, A.A method is developed for the calculation of the aerodynamic forces acting on a ‘swallow tail’ wing of small aspect ratio. Lift, induced drag, and aerodynamic centre position of simple swallow tail wings (Fig. 1 (b)) are computed as an application. For a given incidence, lift and induced drag are, within the limits of the theory, proportional to aspect ratio and independent of speed. The chordwise life distribution rises linearly from zero at the apex, drops rapidly in the region of the root chord trailing edge, and then decreases gently to zero.Item Open Access Aeroplane design studies conventional and V.T.O.L. freighter aircraft (Academic Years 1959 and 1961)(College of Aeronautics, 1963-11) Howe, D.During the second year of their course in the Department of Aircraft Design, students have the option of working as a member of a team engaged in a design study. The subjects for the studies are chosen to represent the current interests of the industry and include unusual features considered to be worthy of investigation. Examples of these design studies are the F-59 freighter and its derivative the F-61, V. T.O. L. freighter. In a conventional role these designs are intended to carry a payload of up to 77000 lb. , over 800 nautical miles range, using four turboprop engines. V. T.O. L. capability is given to the F-61 design by the addition of two wing pods, each of which houses 22 lift engines. The application of boundary layer control in the form of blown ailerons and flaps has been investigated for the F-59 design. Both aircraft have been designed in detail. The major conclusion of the studies is that the application of V. T.O. L. to large freight aircraft is feasible, but further detailed work is necessary to resolve some flutter and noise problems.Item Open Access Aeroplane design studies mach 2.2 and mach 3.0 supersonic airliners (academic years 1960 and 1962)(College of Aeronautics, 1965-02) Howe, D.This report is divided into three parts. The first two of these describe the A-60, Mach 2.2 airliner and the A-62, Mach 3.0 airliner design studies respectively. Apart from the different cruise speeds these two aircraft were designed to meet the same basic requirements and the third part of the report is a comparison of them. The Mach 2.2 design was based upon the use of a slender, integrated, delta layout with six turbojet engines buried in the rear fuselage. It was intended to carry up to 120 passengers over transatlantic ranges. Although the chosen engine installation enabled a compact aircraft to be designed it did introduce severe structural and installation difficulties. A canard delta arrangement was proposed for the Mach 3.0 aircraft. Drooping of the wing tips for supersonic flight was found to confer important stability advantages without introducing an unacceptable weight penalty. The steel structure was designed around the use of both corrugated reinforced and honeycomb sandwich skins, the former being preferable. An interesting feature was the choice of a sealed, cryogenic, environmental control system. This was found to be very attractive but as it proved to be somewhat heavier than anticipated it is suggested that a good compromise could be obtained by using a more conventional system for subsonic flight phases. The major conclusion from the comparison between the two study aircraft was that in many respects there is very little to choose between them. However the Mach 2.2 aircraft represents a more logical step from existing airliner designs and presents fewer materials problems. As it is comparable economically it represents a better choice for a first generation supersonic design.Item Open Access Aeroplane design studies: bpropeller turbine and pure jet powered general purpose transport aircraft (academic years 1963 and 1965)(College of Aeronautics, 1967-05) Howe, D.The recent interest in the air bus conception of air travel is reflected in the aircraft chosen for study by the students in the Department of Aircraft Design during the 1963 and 1965 academic years. The first study was based upon the use of four propeller turbine engines to power an aircraft capable of carrying up to 40,000 lb. of payload over short stage lengths. Emphasis was placed on the need for operations with mixed passenger and freight loads and the fuselage layout incorporates two decks, the lower one of which is designed as a freighthold with nose loading doors. The second study was similar except that four wing mounted pure jet engines replaced the propeller turbines of the earlier design. The cruising speed is thus some 50 per cent higher with a Mach number limitation of 0.8. The two deck fuselage layout is retained, but with a rear loading door for the freighthold, and the wing has 28° of leading edge sweepback . An initial economic comparison of the two aircraft revealed that when the aircraft are operated over 250 n. mile stage lengths the direct operating costs of the propeller turbine powered design are some 20 per cent less than those of the pure jet version. This is mainly due to the much lower first cost of the simpler aircraft.Item Open Access Aeroplane design study STOL airliner (A71). Part 1- configuration description and data(Cranfield Institute of Technology, College of Aeronautics, 1972-06) Howe, D.; Ward, R. E.The interest in STOL airliners was reflected in the choice of a 100-118 passenger short range aircraft of this type as the 1971 design project. In addition to the use of the study for detailed investigation by the students of Aircraft Design it also served as the basis for an investigation of the low speed lift and control problems of STOL aircraft. This report is concerned with a description of the configuration adopted and specification of geometric and aerodynamic data. As such it is the first part of the complete reporting of the investigation, subsequent parts being concerned with the more detailed work. The aircraft was designed to operate from 2000 ft long single runways and have a cruising speed of up to 11 - 0.83 at 30,000 ft altitude. The estimated gross weight is 115,000 lb and when landing at 100,000 lb weight the approach speed is 79 knots. The high lift coefficients necessitated by this are obtained either by externally blown jet flaps or an augmenter wing arrangement.