The purpose of the work described in this report was to study the effect of longitudinal pressure gradients upon compressible turbulent boundary layers on a flat plate, with and without air injection. A brief survey of ...
Experimental data are presented for the development of compressible turbulent boundary layers moving from a solid onto a transpired surface, and vice versa. The data were obtained at free stream Mach numbers of 1.8 and 3.6 ...
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 phenomenon known as 'air resonance', peculiar to helicopters with hingeless rotors, has been analysed and presented in as simple a manner as possible. In the air resonance case the 'body mode' with frequency close to ...
The head measurements obtained during the 1970/1971 anthropometric survey of 2000 Royal Air Force aircrew have been processed to provide size-roll data in a form suitable for use by headgear designers. Specimen size-rolls ...
Two aspects of the solution of the equations governing steady gas flow in a laminar boundary layer, when the main stream velocity is non-uniform, are considered. In the first place it is shown that the equations can be ...
Time marching methods are in principle the most flexible means of calculating blade-to-blade flows in turbomachinery since the same method can be used for subsonic, transonic and supersonic flows with automatic inclusion ...
An anthropometric survey of 500 R.A.F. aircrew heads was undertaken in 1972. 45 measurements were taken from each subject. Data obtained from these, together with those from 17 derived measurements, are presented in the ...
C. B. Bolton; M Kenward; R. E. Simpson; G. M. Turner(1973)
The survey was undertaken to provide up-to-date information on the body measurements of Royal Air Force aircrew. This information is required for cockpit workspace and functional-clothing-sizing studies. A team of two ...
The noise levels produced by hot and cold subsonic jets have beefi measured using a convergent circular nozzle in an anechoic chamber. This report presents the effects of jet temperature on the sound power, the overall ...
Rays from a moving sound source are traced through a regular array of convected vortices (representing a turbulent jet) and also through the corresponding mean shear flow. The far-field intensity is compared in the two ...
The development of an adaptation to flight of the 'oil-flow' technique of visual!sing the surface flow is described as applied to a slender-wing research aircraft. The technique yielded repeatable results which, when ...
Non-linear oscillatory-motion histories, measured in the R.A.E. wind-tunnel/flight-dynamics simulator, are analysed. The resulting dynamic-motion characteristics for large-amplitude motions in the pitch plane are discussed ...
A technique is presented for condensing a multi-degree-of-freedom flutter calculation so that similar flutter conditions are achieved with two degrees-of-freedom. Use is made of digital computer programmes, and the process ...
The tests were made by replacing the existing centre six thick vanes at the first corner of the 4 x 3-ft wind tunnel by vanes of sheet metal. The thin vanes reduced the-corner loss, estimated from a wake traverse behind ...
The author's treatment of the Mangler and Smith vortex-sheet model of leading-edge separation is extended to the calculation of steady conical flow past a yawed slender delta wing. Introducing yaw destroys the symmetry ...
PART I The Mechanism of Damping Factor. PART II Meridional Flow Calculations. PART III Blade-to-Blade Flow Calculations. Part I of the report exposes the dependence of asymptotic numerical convergence upon the eigenvalues ...
THE TECHNICAL REPORTS published by the Aeronautical Research Council in the Reports and Memoranda Series have been so numerous that separate indexes to them have at times been published. Two Combined Indexes to the Technical ...
The probe decelerates a portion of the supersonic free stream into the subsonic range within a distributed compression fan. Stagnation pressure is sampled in the region of subsonic flow using a pitot tube. Pressure recovery ...
The report describes an experiment made jointly by an Anglo-French team to determine unsteady pressure distributions and forces on a low aspect ratio wing with an oscillating control surface. Two series of tests were made ...