Browsing by Author "Nonweiler, T."
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Item Open Access The air resistance of racing cyclists(College of Aeronautics, Cranfield, 1956-10) Nonweiler, T.Tests in the closed-section wind-tunnel on three different cyclists mounted on a racing bicycle are described, and figures quoted for the recorded air resistance. Some comments are also included on the implications of the results concerning the power-output of racing cyclists.Item Open Access Incompressible flow past bodies of revolution(College of Aeronautics, 1955-07) Nonweiler, T.In this paper we shall attempt to review the existing information, both theoretical and experimental, which relates to same of the more important aerodynamic problems arising in the study of the flaw over bodies of revolution. Many of these problems can only be explained by including an account of the effects of the air viscosity on the flow, but this can more easily be accomplished if we first consider the simpler conditions existing in inviscid, irrotational flow. In common with many other branches of aerodynamics, potential flaw theory provides a basic framework of knowledge, helping to suggest likely effects of viscosity, which we can modify to explain, and predict the behaviour of a real fluid. Thus the first part of this paper is taken up with a study of the various methods which have from time to time been devised to enable the calculation of the properties of axisymmetric potential flow. Tie shall first concern ourselves with more or less exact, rigorous theories, and afterwards 1.1th the approximate methods. Space does not permit a full discussion of the exact techniques but it is not considered that any single approach possesses advantages above all others to warrant exclusive attentions so a brief review is given of most of those which have been developed. The theory of potential flat about inclined bodies of revolution is next discussed, and leads to an account of the manner in which these results can be used to derive the surface pressure distribution, and the magnitude of the theoretical destabilising moment on a body in a simple translational motion ... [cont.].Item Open Access The laminar boundary layer in slip flow(College of Aeronuatics, Cranfield, 1952-11) Nonweiler, T.This report discusses the effects of the existence of a small, but finite, molecular mean-free-path on the steady air flow in the laminar boundary later. The boundary conditions at the exposed surface are modified by the existence of a slip velocity and temperature-jump between the air and the surface, and a theory of first-order approximation is developed to account for the consequent modification to the shear stress and heat flux to the surface. Continues…Item Open Access The man-propelled aircraft: a preliminary assessment(College of Aeronautics, 1956-03) Nonweiler, T.1. Introduction It is the intention of this note to set down a few tentative, but (it is hoped) realistic, assessments of the problems involved in the design of an aircraft which by the crew's own muscular efforts shall take off from the ground and sustain steady flight, for a short period. The desire to fly is one of the oldest dreams of mankind, and it has of course found partial fulfilment with the help of external sources of power : but the ultimate achievement of unaided flight is yet to be realised. Everest was "conquered" with the help of the internal combustion engine in 1933 ; but the ultimate achievement was the greater glory of 1954. If the conclusions of this paper are correct, man-powered flight can surely be another "crowning glory" very soon. These conclusions may of course be incorrect; the amount of work done hardly justifies unqualified confidence in their truth. Yet a useful purpose will be served by this note if it causes sufficient enthusiasm or distrust to stimulate researches by those better qualified than the author to dogmatise on many of the aspects of the problem treated...[cont.].Item Open Access A method for numerical evaluation of the integral...(College of Aeronautics, Cranfield, 1956-03) Nonweiler, T.This report presents formulae and data for the numerical evaluation of the double integral named in the title...Item Open Access The numerical solution of certain differential equations occurring in Crocco's theory of the laminar boundary layer(College of Aeronautics, Cranfield, 1953-05) Kirkby, S.; Nonweiler, T.A numerical method is described for the solution of certain differential equations which result from the application of Crocco’s transformation to the laminar boundary layer equations appropriate to high supersonic Mach numbers. (i.e. at hypersonic speeds). Continues …Item Open Access A resume of maximum lift data for symmetrical wings, with various high-lift aids(College of Aeronautics, 1954-03) Nonweiler, T.We shall attempt here to summarise the existing data on the values of the low-speed CLmax of wings, in the absence of a fuselage, and without including information on stalling incidence or pitching moment. The summary is limited to the consideration of unswept wings, and those of delta planforms, which have symmetrical sections: there is some discussion of the maximum lift increments due to the use of flaps of various kinds.Item Open Access Skin temperatures and heat transfer over wedge wings at extreme speeds of flight(College of Aeronautics, Cranfield, 1956-08) Nonweiler, T.By paying spacial attention to the wing design and altitude of flight, it is possible to ensure that the highest temperature reached at the leading edge of the wing of an aircraft, in level flight at speeds of the order of the circling velocity, need be no more than about 1000*c.Item Open Access Surface conduction of the heat transferred from a boundary layer(College of Aeronautics, Cranfield, 1952-05) Nonweiler, T.This note considers the effect of thermal conductivity upon the temperature distribution in the skin of a body (moving through air) due to the heat transferred from the boundary layer. It is found that the effects are of importance only very near the nose of the body, and that here the temperature reaches a maximum which, depending on the skin conductivity and thickness, may be appreciably less than the thermometer temperature, particularly at high speeds and altitudes of flight.Item Open Access Theoretical stability derivatives of a highly swept delta wing and slender body combination(College of Aeronautics, Cranfield, 1951-11) Nonweiler, T.The stability derivatives of a delta wing of small aspect ratio, mounted on a cylindrical body with a slender pointed head, are derived by considering the flow in planes perpendicular to the body axis to be uninfluenced by the change in the streamwise component of the air velocity (the so-called ‘slender body’ theory).Item Open Access The theoretical wave drag at zero lift of fully-tapered swept wings of arbitrary section(College of Aeronautics, Cranfield, 1953-10) Nonweiler, T.An expression is deduced for the wave drag of a fully tapered swept wing of arbitrary section in the convenient form of a double integral involving the variation of wing-surface slope. It is concluded, in the general case, that the drag may best be computed by numerical integration, the method for which will be the subject of a further report. Continues …Item Open Access The two-dimensional laminar boundary layer at hypersonic speeds(College of Aeronautics, Cranfield, 1953-01) Nonweiler, T.A numerical solution is found for the equations governing the motion of a two-dimensional laminar boundary layer, in the absence of a pressure gradient, which would be valid if the flight Mach number is very high (i.e. M2>>1). The effects of surface slip, and the finite thickness of the boundary layer are shown to be negligible if the Reynolds Number (R) exceeds about 105, and are neglected. Continues …Item Open Access The wave drag of highly-swept wings: a comparison of linear theory and slender body theory(College of Aeronautics, 1954-10) Nonweiler, T.This note comments on the comparison between the answer obtained by linear theory for the wave drag of slender-wings (as interpreted by the limit and that value for the drag obtained by Slender-Body Theory. It is shown that for fully tapered wings the agreement is exact, and that there is reason to suppose that the same is true for all wing planforms, unless the trailing-edge is unswept, or the wing section has a finite trailing-edge thickness. Some remarks are included concerning the drag of slender delta wings.