An introduction to vortex breakdown and vortex core bursting

This report is an introduction to the phenomenon of vortex breakdown, also know as vortex core bursting. The first part of the report presents some important elements of basic vortex theory. The second part reviews the research that has been done on vortex breakdown, including an overview of the historical development of vortex breakdown...

An improved numerical method for solving the transonic small-perturbation equation for the flow past a lifting aerofoil

Improvements have been made in the method proposed by Murman and Cole¹ and by Krupp² for solving the transonic small-perturbation equation for the flow past a lifting aerofoil. The basic equations, the boundary conditions and other conditions are first set down, with some brief comments. An account of the numerical method follows, with...

A fracture of rubber in a state of finite torsional shear

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 pressure distribution over the flat end surfaces of compressed solid rubber cylinders

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.

A study of the stress distributions necessary to maintain rubber in a state of torsion

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.

Studies of pure homogeneous deformations in unfilled natural and butyl rubbers

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.

A numerical method for solving the equations for a vortex core

A method is presented for calculating steady axially symmetric spiralling motions of an incompressible fluid at large Reynolds numbers. By making approximations of the boundary-layer type the Navier-Stokes equations are reduced essentially to a pair of non-linear parabolic equations. Initial conditions are specified on some upstream cross...

An experimental investigation of contoured nose orifices with ejection at free-stream mach numbers of 1.86 and 4.3

Gas was ejected from an orifice in the nose of three different axi-symmetric models to investigate whether, by suitable contouring of the orifice, a fully attached flow could be obtained in a supersonic stream. Spark shadowgraphs and measurements of surface static pressure and of the total temperature, total pressure and mass flow of the ejected...

A comparison of the measured and predicted flutter characteristics of a wing-aileron-tab model

The paper presents results of wind tunnel flutter tests using a wing-aileron-tab model on which it was possible to represent any of the following tab systems; spring, geared, trim or servo. Prediction of the flutter characteristics has been made in the trim tab case using three sets of aerodynamic derivatives and fair agreement has been reached...

A numerical method for calculating inviscid vortex cores

A numerical method is presented for solving the equations of motion for axially symmetric flows of an incompressible, inviscid but rotational fluid. The method of solution is to replace derivatives in the axial direction by finite differences and then to solve the resulting set of ordinary non-linear differential equations by the Runge-Kutta...

Boundary layers in three dimensions

Some of the recent advances in the theory of three-dimensional boundary layers are the subject of this paper, which is in three main parts. The first part consists of general considerations. The boundary layer equations for laminar compressible flow, and the corresponding momentum integral equations, are written down, in an orthogonal...

Analysis of acantilever beam developing an isoplastic response under impact at the tip

A condition of isoplasticity is defined for a beam as the development of plastic strains simultaneously at all points along the profile fibers. Two conditions must be satisfied simultaneously, one on the profile shape, and one on the mass distribution. It appears that the second condition can only be approximately satisfied if there is a...

A preliminary analysis of the penalties associated with piercing a wing torsion box with a grid of holes

This analysis relates to a conventional aircraft that is modified by the addition of fans housed in the wing plane to provide means for vertical take-off and landing. The influence of a grid of holes in the wing torsion box, on top level speed, is inferred by the torsional stiffness criterion for wing divergence. The probable weight penalty...