Kelvin's circulation theorem is applied to compressible flow through a cascade of blades and expressions are derived for the three streamwise components of vorticity at exit from the cascade. Calculations show that for a ...
The Navier-Stokes equations for the flow of a viscous incompressible fluid through curved pipes of different sections are solved in power series of the curvature of the pipe. The solution is given as far as the first power ...
This note gives examples and photographs of several structural defects which have occurred in service and shows that, although many failures may be due to fatigue or the application of excessive static-loads, some are ...
A method is developed for designing the centre portion of a cambered and twisted swept-back wing to have the same chordwise load distribution at all spanwise stations. For this purpose the downwash field induced by a doublet ...
A review is presented of the shear buckling of isotropic and orthotropic plates with a detailed consideration of the latter. An extensive bibliography is given and the details of the analyses in these papers are also ...
An analysis is made of the shear deformation of a corrugated web attached to the flanges at discrete points. The shear stiffness is calculated for a wide variation of the dimensions of the web, and two positions of the ...
In simple harmonic oscillation of the helicopter with hinged blades, the tip-path plane is tilted with respect to the shaft in the plane of oscillation and in the plane perpendicular to it. The angles of tilt can be expressed ...
The methods of classical aerofoil theory are used to derive a general theory for wings of any given plan form. Accordingly, the general downwash equation is split into two parts : one, the effective incidence, being due ...
This note gives a convenient method of obtaining CD from a pitot-static traverse in an aerofoil wake, using Jones' equation as modified by Lock, Hilton and Goldstein for compressible flow. Charts are provided from which ...
A method, alternative to that in common use at present, of calculating the response quantities in pull-out manoeuvres relevant to important cases of loads and stresses in aeroplane structures, is presented. The method, ...
A flat plate containing a circular hole is subjected to arbitrary bi-axial stresses at infinity; adajcent to the hole and bonded symmetrically to both sides of the plate are cylindrically wound fibre composite annular ...
This note shows how the Hill Aero-isoclinic Principle works out in practice for a swept wing, fixed at the root and having straight flexural and inertia axes. The conditions assumed are readily represented in a wind-tunnel ...
A piloted flight simulator study of the low speed handling of the BAC 221 slender-wing research aircraft was performed for validation of the simulation of slender-wing supersonic transport aircraft. The lateral representation ...
Summary. This Report describes a fixed-base simulator investigation of the rolling requirements for two types of aircraft on the landing approach. A small trainer/strike aircraft, and a large transport aircraft are simulated, ...
The paper gives a theory of vortex flow in turbo-machines in which the basic assumption is made that the axial-velocity profiles always belong to a family governed by a single parameter, λ. This parameter is a measure of ...
To investigate the basic aerodynamic characteristics of jet-flap aircraft, six-component force and moment measurements have been made on jet-flap complete models in the R.A.E. No. 2 11½ ft x 8½ ft low speed wind tunnel. ...
The effect of a spawise surface corrugation on the position of transition from laminar to turbulent flow in the boundary layer of an aerofoil depends on the local disturbances caused by the corrugation and on the stability ...
The report, which has been written as a preliminary to a later account of similar work in lifting-plane theory, describes how wing loading problems involving discontinuities are solved by lifting-line theory. The four ...
The report describes in detail the methods by which the principles of vortex-lattice theory, introduced in a previous report, R. & M. 1910, are applied to the calculation of the aerodynamic loading of wings by lifting-plane ...
The laminar boundary-layer equation, for a linearly retarded velocity in the main stream, U = 1 - 1/8x in reduced variables, has been solved numerically by working in finite intervals in x, with a correction for the finite ...