Browsing CoA. Reports by Publication Date

On the analysis of statically indeterminate structures

Hemp, W. S. (College of Aeronautics, Cranfield, 1946-11)

This report develops a general method for the analysis of statically indeterminate structures. It concerns itself both with a rigorous demonstration of the validity of the methods and with recommendations for their successful ...

Ignoration of distortional co-ordinates in the theory of stability and control

Duncan, W. J. (College of Aeronautics, 1946-12)

Gates and Lyon have proposed to treat theoretically the stability and control of deformable aircraft by a method in which the distortion co-ordinates are ignored and the influence of distortion is allowed for by suitable ...

Note on the application of the linearised theory for compressible flow to transonic speeds

Robinson, A.; Young, A. D. (College of Aeronautics, Cranfield, 1947-01)

It is shown that for finite aspect ratio the linearised theory of compressible flow remains theoretically consistent in the region of transonic speeds, although tis predictions may deviate appreciably from experimental ...

Technique of the step-by-step integration of ordinary differential equations

Duncan, W. J. (College of Aeronautics, Cranfield, 1947-02)

In Part 1 step-by-step methods are examined critically and emphasis is placed on the dependence of the error on the number n of steps used for a given range of the independent variable. The index of a process is defined ...

Note on the dynamics of a slightly deformable body

Hemp, W. S. (College of Aeronautics, Cranfield, 1947-02)

The purpose of this note is to develop the equations of motion of a slightly deformable body. Appeal to general principles shows the independence of the translation (Para.2). Moving axis are defined in papa.3 which can be ...

The effect of the sweepback of delta wings on the performance of an aircraft at supersonic speeds

Robinson, A.; Davies, F.T. (College of Aeronautics, Cranfield., 1947-03)

The variation with sweepback of total drag of an aircraft in level flight at supersonic speeds is calculated. It is shown that sweepback is not uniformly beneficial, but that in general the optimum amount of sweepback ...

Wing body interference at supersonic speeds

Kirkby, S.; Robinson, A. (College of Aeronautics, Cranfield, 1947-04)

The increment in lift due to wing-body interference at supersonic speed is calculated approximately for an untapered wing without sweepback.

Note on the velocity and temperature distributions attained with suction on a flat plate of infinite extent in compressible flow

Young, A. D. (College Of Aeronautics, Cranfield, 1947-08)

The problem considered by Griffith and Meredithl for incompressible flow is here considered for compressible flow, it being assumed that there is no heat transfer by conduction at the plate. Essentially, the method consists ...

Application of the linear perturbation theory to compressible flow about bodies of revolution

Young, A. D.; Kirkby, S. (College of Aeronautics, Cranfield, 1947-09)

The linearised theory is developed in some detail in order to clarify the differences between two-dimensional and axi-symmetric flow. In agreement with other authors it is concluded that the perturbation velocity on a thin ...

Source and vortex distributions in the linearised theory of steady supersonic flow

Robinson, A. (College of Aeronautics, Cranfield, 1947-10)

The hyperbolic character of the differential equation satisfied by the velocity potential in linearised supersonic flow entails the presence of fractional infinities in the fundamental solutions of the equation. Difficulties ...

Bound and trailing vortices in the linearised theory of supersonic flow, and the downwash in the wake of a delta wing

Robinson, A.; Hunter-Tod, J. H. (College of Aeronautics, Cranfield, 1947-10)

The field of flow round a flat aerofoil at incidence can/may be regarded in linearised theory as the result of both bound and trailing vortices for supersonic as well as for low speed flight. This leads to a convenient ...

The aerodynamic derivatives with respect to sideslip for a delta wing with small dihedral at supersonic speeds

Robinson, A.; Hunter-Tod, J. H. (College of Aeronautics, 1947-12)

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 ...

Assessment of errors in approximate solutions of differential equations

Duncan, W. J. (College of Aeronautics, Cranfield, 1947-12)

The term assessment is applied to any process which enables us to set rigid bounds to the error or to estimate its value. It is shown that upper and lower bounds can be assigned whenever the Green's function of the problem ...

Skin friction in the laminar boundary layer in compressible flow

Young, A. D. (College of Aeronautics, 1948)

On a theory of sandwich construction

Hemp, W. S. (College of Aeronautics, 1948-03)

The theory of sandwich construction developed in this paper proceeds from the simple assumption that the filling has only transverse direct and shear stiffnesses, corresponding to its functional requirements (§1). This ...

Note on the limits to the local Mach number on an aerofoil in subsonic flow

Young, A. D. (College of Aeronautics, 1948-04)

It has been noted in some experiments that the local Mach number just ahead of a shock wave on an aerofoil in subsonic flow is limited, values of the limit of the order of 1.4 are usually quoted. This note presents two ...

On some problems of unsteady supersonic aerofoil theory

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 ...

The relative accuracy of quadrature formulae of the Cotes' closed type

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. ...

On the integration of hyperbolic differential equations

Robinson, A. (College of Aeronautics, Cranfield, 1948-07)

See full text for abstract.

Flutter of systems with many freedoms

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 ...

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