Browsing by Publication Date

Browsing by Publication Date

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  • Kirkby, S. (College of Aeronautics, Cranfield, 1948-05)
    Quadrature formulae, such as those discovered by Gregory, Newton, Simpson and Cotes, which are derivable by integration of Lagrange’s interpolation formula between definite limits, are classified as Cotes’ Type Formulae. ...
  • Robinson, A. (College of Aeronautics, Cranfield, 1948-05)
    Unsteady supersonic flow round an aerofoil of infinite span is considered in the first part of the paper.It is shown that the pressure at any given point of an aerofoil under forward acceleration can be analysed into three ...
  • Robinson, A. (College of Aeronautics, Cranfield, 1948-07)
    See full text for abstract.
  • Duncan, W. J. (College of Aeronautics, Cranfield, 1948-08)
    Experience has shown that it is often necessary to retain many degrees of freedom in order to calculate critical flutter speeds reliably, but this entails much labour. Part 1 discusses the choice of a minimum set of freedoms ...
  • Morley, A. W. (College of Aeronautics, Cranfield, 1948-09)
    The efficiency of a process of compression or expansion of a gas is commonly defined in terms of the change in energy which occurs as compared with the change required in isentropic flow. In another method the efficiency ...
  • Morley, A. W. (College of Aeronautics, Cranfield., 1948-09)
    This note records some calculations of the efficiency of adiabatic shock in air (x=1.4); where the efficiency is defined as the ratio of the work used to compress the air in the shock wave, from the inlet static to the ...
  • Young, A. D. (College of Aeronautics, 1948-10)
  • Lilley, G. M. (College of Aeronautics, Cranfield, 1948-12)
    There is a need for high speed wind tunnels of modest dimensions and costs in establishments teaching the fundamentals of compressible flow. This paper discussed briefly the layouts and performances of various types of ...
  • Hemp, W. S. (College of Aeronautics, Cranfield, 1949-03)
    This report is concerned with the calculations of the natural frequencies of an ideal structure somewhat representative of an aircraft fuselage. The results are based upon a simplified “shell” theory which permits proper ...
  • Lilley, G. M.; Holder, D. W. (College of Aeronautics, Cranfield, 1949-03)
    The performance of an induction type high speed wind tunnel driven by low pressure steam (up to 120lb. per sq.in. absolute) has been investigated up to a Mach number of about 1.7. It was found that by suitable design a ...
  • Hunter-Tod, J. H. (College of Aeronautics, Cranfield, 1949-03)
    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 ...
  • Hunter-Tod, J. H. (College of Aeronautics, 1949-03)
    This paper treats the elastic stability of supported rectangular plates of sandwich construction with isotropic and aeolotropic fillings under compression and shear loading. Formulae are developed for critical stresses ...
  • Duncan, W. J. (College of Aeronautics, Cranfield, 1949-04)
    Two simple means for establishing a relation between a pair of oscillation problems are briefly discussed. In the first, the displacements are connected by use of a differential operator. The set of natural frequencies is ...
  • Hemp, W. S.; Griffin, K. H. (College of Aeronautics, Cranfield, 1949-06)
    A simplified panel model is described, together with a number of assumptions about the mode of its bucking. The approach to the calculation of the buckling stress is by splitting the panel into a number of flat plates and ...
  • Stanley, P. J. (College of Aeronautics, Cranfield, 1949-07)
    During the war, the rate of production which could be expected from an organisation setting out to manufacture a new type of aircraft was of great interest from the planning point of view. It was found that a time of the ...
  • Stanton Jones, R. (Cranfield College of Aeronautics, 1950-01)
    This paper describes the derivation of empirical formulae for the loading distribution on straight tapered swept back wings, in terms of the parameters governing the geometric wing plan form. The derivation is based mainly ...
  • Hemp, W. S. (College of Aeronautics, Cranfield, 1950-01)
    The object of this report is two-fold. On the mathematical side it seeks to illustrate the use of oblique coordinates in applications to Elasticity and Structure Theory. On the practical side it seeks to provide methods ...
  • Duncan, W. J. (College of Aeronautics, Cranfield, 1950-01)
    It is shown that the rate of subsidence or divergence ﮑ of a system which is near a state of neutral static stability can easily be calculated for knowledge of the mode of displacement in the neutral state and this model ...
  • Lewis, S. R. (College of Aeronautics, Cranfield, 1950-02)
    This report extends the work of W. J. Goodey, and gives numerical examples of the shear distribution around a frame subjected to a single concentrated radial load for variations in the parameters, such as, frame stiffness, ...
  • Dowlen, E. M. (College of Aeronautics, Cranfield, 1950-04)
    The profile drag-coefficients of a number of low-drag wings with straight trailing edges have been calculated. A comparison is made with other low-drag and conventional sections which indicates an increase in profile ...