Experiments are reported of the self-preserving turbulent corner wall jet formed by directing a jet of air parallel to the line of intersection of two walls abutting at right angles. Self preserving profiles of the mean and turbulent flow are established by approximately 50 jet diameters downstream. Like the three-dimensional wall jet on a plane-wall surface there is evidence of a significant secondary flow induced by vortex line bending, though its magnitude is smaller than in the plane-wall case.

Buckling equations for stiffened cylinders under the specified loading are formulated and solved by means of double Fourier series using the Galerkin process to reduce the solution to the standard algebraic eigen-value problem. Matrices of order 80 by 80 are required for convergence reflecting the complexity of the mode shape describing the buckling patterns.

Simple design curves are developed for determining buckling loads of monocoque cantilever loaded cylinders.

Excellent agreement with test values is demonstrated, indicating that the cylinders are not highly sensitive to imperfections, as is the case of the uniform, axially loaded cylinder. This also follows from the fact that considerable post buckling strength exists for the cantilever loading condition.

The estimation of the relative orders of the coefficients in the linear differential equations of longitudinal small perturbation of aircraft is used to analyse the classical simplified theory for the short- and long-period modes by the singular perturbation methods. The leading terms of the asymptotic expansions give the eigenvalues for short- and long-period modes with fairly good accuracy, except that the damping part of the eigenvalue for the long-period mode has relative error of the order of 10%. These approximate eigenvalues are improved by the method of strained co-ordinates which accounts for most of the differences. The dynamic response due to initial disturbances of velocity, angle of attack, and angle of pitch are also derived.

The separation of boundary-layer flow from a wing or in a diffuser usually defines the limit of efficient operation, so it is important that the onset and development of separated flow can be predicted. The calculation of the interaction of the shear layout close to an aerofoil with the external inviscid flow has offered an attractive alternative to solving the Reynoldsaveraged Navier Stokes equations for attached flow: the interaction method is much faster. In this paper it is shown how the interaction approach can be extended for use with separated flows and the development of a practical method is described. The calculation of the shear layer through the singularity at separation is accomplished by using an inverse mode. Beyond separation the empirical definition of a new family of velocity profiles allows an integral calculation of the shear layer to proceed up to the reattachment. The solutions for the shear layer close to the aerofoil are matched to the external inviscid flow by a ‘semi-inverse’ method. A careful examination of the stability of this method leads to rapid convergence for separated and attached flows. As an illustration the stall and post stall behaviour of a twodimensional aerofoil is predicted and compared with experimental results.