Root-mean-square intensities and spectra of local pressure fluctuations were measured by transducers at two positions on the inner part of the wing and four on the outer part, while low-frequency pressure fluctuations on ...
CONTENTS: Spring Tabs on Frise Ailerons. Why Shear Webs? A Boundary Value Problem for a Hyperbolic Differential Equation Arising in the Theory of the Non-uniform Supersonic Motion of an Aerofoil. A Study by a Double-refraction ...
Summary. The Report examines the feasibility of improving hovering control of unstabilized jet-lift aircraft by reshaping stick commands. From basic theoretical considerations it is shown that the open-loop properties of ...
An extensive series of mean velocity measurements on the incompressible turbulent boundary layer with distributed injection is described. Boundary-layer developments have been measured along a porous flat plate under a ...
Summary. An analysis is given for the potential flow through a cascade in which a change in axial velocity occurs. An approximate solution of the derived potential equation is obtained and applied first to a flat plate ...
Summary. A method is described for finding asymptotic solutions, valid for large time, of a certain class of linear, integro-differential equations which typically arise in the description of systems exhibiting heredity. ...
The influence of a uniformly reinforced 'rounded-square' hole on the stress field in an infinite sheet is examined. Stress concentration factors are presented in graphical form for a wide range of corner quadrant radius ...
Summary. In this Report a method of obtaining the transient solution of the helicopter rotor blade flapping motion is developed and the effective damping of the motion determined for tip speed ratios up to unity and above. ...
The two-dimensional surface giving minimum pressure drag for given lift coefficient in supersonic flow is considered. The method adopted is a small perturbation of a plane surface; the pressure is expressed as a power ...
A theoretical analysis is made of the equilibrium temperature distribution in the vicinity of the leading edge of a wing of a very high speed aircraft. Results are presented for thermally non-conducting leading edges and ...
This report deals with the development of a technique for direct recording of the attitude of an aircraft relative to-flight path during dives, i.e., the direction of incidence of free airflow relative to aircraft datum, ...
D. J. L. Smith; I. H. Johnston; D. J. Fullbrook(1967)
Part I - The design of a turbine stage is described in which all leading parameters (stage loading, flow coefficient, pitch/chord ratio, blade profile shape and aspect ratio) have been selected conservatively to accord ...
In this Report the details are given of the results of measurements of mean values in time of pitot pressure and flow direction made in the boundary layer over the insulated side-wall of a specially constructed supersonic ...
The performance of a turbo-jet engine has been measured, and alternative methods of determining gross thrust and air mass flow calibrated in a ground level static test bed and an altitude test bed simulating flight conditions. ...
Summary. A method is presented for designing the lower surface of a lifting configuration for high supersonic speeds using the known flow field behind an axisymmetrical conical shock wave. The leading edge can be prescribed ...
Summary. The equations of motion for supersonic flow over a symmetrical wing at zero incidence are linearised and the pressure coefficient at a point in the wing mean plane is expressed in terms of the finite part of a ...
A computer programme has been written to solve the steady laminar two-dimensional boundary-layer equations for a perfect gas at given wall temperature, without wall suction. The programme solves the equations at a blunt ...
The flow of air past an infinite shell is considered. In its undisturbed state the shell is a circular cylinder. A portion of the shell between two normal cross-sections is flexible, the rest of the shell being rigid and ...
Results of propeller whirl analyses in four degrees of freedom are presented for a typical turbo-prop aircraft power-plant installation consisting of a rigid engine supported with elastically restrained freedoms in pitch ...