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 ...
The incompressible second-order theory for two-dimensional aerofoils is extended to finite swept wings. The flow field is represented by distributions of sources and 'lifting singularities' on the 'chord surface' which ...
A lifting surface theory method is described, capable of calculating the loading distribution on swept or slender planforms in attached, subsonic flow. Preliminary numerical results are presented which demonstrate that the ...
The report comprises two contrasting and complementary approaches to the evaluation of the second-order aerodynamic side force and yawing moment on lifting wings when leading-edge and side-edge forces play an important ...
Non-linear partial differential equations that govern the steady supersonic three-dimensional flow of an inviscid ideal gas with constant specific heats in an arbitrary curvilinear co-ordinate space are derived. A special ...
The geometry is given of a probe capable of measuring stagnation pressure directly in a supersonic flow, by means of an isentropic compression. Tests have shown that such a probe can indicate the local stagnation pressure ...
Analytical solutions are derived for a class of axisymmetric base flows with heat addition. The assumed upstream conditions are non-uniform in velocity and temperature, which vary with r in spherical polar coordinates (r, ...
The report presents the results of calculations of torsional flutter of unstalled cascade blades at zero mean deflection and subsonic Mach numbers. Three kinds of flutter are found. Subcritical flutter occurs when no ...
After a general introduction to the longitudinal motion of aircraft over an extended range of angle of attack there follows a wide-ranging investigation of various aspects of the low-speed-deceleration manoeuvre with ...
The investigation covers all combinations of landing speed, coefficient of friction between the tyre and the ground, and harshness of landing, for any type of pneumatic tyre and wheel unit. Particular attention has been ...