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Euler calculations with emphasis on the nonoverlapped composite grid and hypersonic flows
No full textOptimum Mitchell Frameworks for Three Parallel Forces
No full textThe design of Mitchell optimum structures to carry three coplanar forces has been the most popular topic in this field. However, the mathematical technique involved so far has been rather limited in as much as only strictly symmetrical cases have been considered. It is the intention of the present paper to apply the general theory of optimum design to a rather complicated problem of this type, and study in full detail the outcoming mathematical concepts, both numerical and theoretical
The drag of source distributions in linearized supersonic flow
No full textMost bodies whose wave drags in supersonic flow have been calculated by linearised theory are such that the flows can be represented by a suitable distribution of sources. The present paper extends this idea by considering the drag problem for the general class of thin and slender bodies which can be replaced by sources only. The flow due to sources is necessarily acyclic, so there can be no local cross-stream forces on such bodies, since their presence would require the introduction of vortex elements
Further tests of a laminar flow swept wing with boundary layer control by suction
No full textPrepared under Ministry of Aviation contract No. KD/18/09/CB63(a
Eurilia (European Initiative in Library & Information in Aerospace) :
No full textThis report is part of the Eurilia (European Initiative in Library and
Information in Aerospace) project, the aim of which is to enhance the Libraries’
R&D and education process which underpins the aerospace sector by establishing a
new service based on a standardised pan- European system for information access,
retrieval, image browsing and document delivery. This will in turn extend the
access and availability of major aerospace collections. The partners in this
project are: University of Limerick, Delft University of Technology, Digital
Equipment Corporation, Sup’Aero, ENSAE - Ecole National Superieure de
l’Aeronautique et de l’Espace, Instituto Nacional de Tecnica Aerospacial,
Cranfield University. This report was originally presented at the international
seminar on Eurilia held at Cranfield University in July 1994. The report was
subsequently submitted to the EC as Eurilia (European Initiative in Library and
Information in Aerospace), Pre-project Audit, Project LIB-EURILIA/3-2083 funded
by the European Action Programme for
Flutter of systems with many freedoms
No full textExperience 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 and suggests that this should be based on the equation of energy and the use of the Lagrangian dynamical equation corresponding to any proposed additional freedom. The method for conducting flutter calculations so as to minimise labour are treated in Part 2
On the application of oblique coordinates to problems of plane elasticity and swept-back wing structures
No full textThe 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 by which designers can solve problems of stress distribution and deflection for the case of swept-back wing structures, whose ribs lie parallel to the direction of flight. Continues
The diffusion of loads in non-rigid circular frames
No full textThis 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, skin thickness, stringer spacing, etc. Continues
Wave reflection near a wall
No full textThe field of flow due to a shock wave or explanation wave undergoes a considerable modification in the neighbourhood of a rigid wall. It has been suggested that the resulting propagation of the disturbance upstream is largely due to the fact that the main flow in the boundary layer is subsonic. Simple models were produced by Howarth, and Tsien and Finston, to test this suggestion, assuming the co-existence of layers of uniform supersonic and subsonic main stream velocities. The analysis developed in the present paper is designed to cope with any arbitrary continuous velocity profile which varies from zero at the wall to a constant supersonic velocity in the main stream. Numerical examples are calculated and it is concluded that a simple inviscid theory is incapable of giving an adequate theoretical account of the phenomenon. The analysis includes a detailed discussion of the process of continuous wave reflection in a supersonic shear layer