Laser doppler velocimetry measurements in coaxial, co- and counter-swirling, isothermal jets

The theoretical performance of optimised glide-path controllers for the Comet IIIB

Two experimental glide-path controllers have been designed for the Cornet lllB aircraft, using a parametric optimisation procedure. Their theoretical performance in the presence of all known disturbances is discussed in detail and compared with that of a controller currently in use with this aircraft. Both controllers show considerable...

Assessment of changes in collision risk of North Atlantic air traffic from changes in the reported sighting rate

The aim of this study of air traffic on North Atlantic tracks is to examine whether an increase in the reported sighting rate of aircraft, identified as straying from an adjacent track, can be used for estimating a change in lateral collision risk, i.e. in the risk which is due to imperfect track-keeping. It is found that the ratio of the...

Aerofoil theory for swallow tail wings of small aspect ratio

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...

Wave reflection near a wall

The field of flow due to a shock wave or expansion 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...

On the Integration of Hyperbolic Differential Equations

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

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

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...

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

The field of flow round a flat aerofoil at incidence can 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 method, given the lift distribution over an aerofoil, for calculating the flow round it at supersonic speeds. As an application of...

On source and vortex distributions in the linearised theory of steady supersonic

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

Wing body interference at supersonic speeds

The increment in lift due to wing-body interference at supersonic speeds is calculated approximately for an untapered wing, without sweepback. The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

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

The variation with sweepback of the 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 depends on the design speed and altitude. The College of Aeronautics was founded in 1946 and was granted university status in...

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

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.