A method for the calculation of the aerodynamic forces on an oscillating aerofoil which allows for the effect of thickness is developed. The steady flow regime for zero or mean incidence is first determhaed for isentropic, ...
In Part I a review is made of helicopter performance after engine failure. The transition from powered operation to autorotation is discussed and a theoretical analysis of the motion is given for a single-rotor helicopter ...
Investigation of the flow between the blade rows in a research compressor with conventional Half-Vortex blades have shown a rapid stage-to,stage build-up of the annulus boundary layer. The axial velocity distribution under ...
To provide data for stressing purposes, measurements have been made of the effect of sideslip on the rolling moment on a 41.5-deg swept-back tailplane mounted at three heights on the fin of a one fifth scale model of a ...
Calculations have been made to find the changes in rotor speed following engine failure in forward flight. Several particular examples were investigated, based on the parameters of the S-81 helicopter. The effect of pilot's ...
The effectiveness of a beam-riding missile is greatly influenced by the mutual effect of noise and nonlinearities. The former is mostly due to radar jitter, while the principal non-linearity is that introduced by limiting ...
The design of axial-flow turbines has been hampered in the past by a lack of comprehensive data regarding pressure losses and gas deflections through rows of turbine blades. In the present report much of the available ...
Control effectiveness tests, using the ground-launched rocket-boosted model technique, have been made on rectangular wings of aspect ratio 4, EC.1250 section, and fitted with a 25 per cent chord concave control flap. Tests ...
Summary.--A reduction method intended for routine use is derived whereby the take-off distance required for a turbo-jet aircraft to clear a 50-ft screen under a specified set of standard conditions of air temperature and ...
This report reviews existing information regarding the behaviour of the local aerodynamic centres of aerofoils, with a view to exposing the more important gaps in our knowledge, and, indicating the lines along which future ...
Some general solutions of the linearised equations of supersonic flow, in terms of Lamé functions, were obtained by G. M. Roper, using the methods of Robinson and Squire. The results were applied to calculate : (a) the ...
Resonance tests on a model cantilever wing carrying concentrated masses were made in conjunction with the flutter tests of R. & M. 2533. Measurements were made with masses up to approximately five times the mass of the ...
The effect of a flexible, geared, elevator tab upon the validity of the stiffness criteria for tail-units and rear fuselages is examined. To this end, the distortions of a hypothetical, semi-rigid tail-unit under the air ...
The flow into a swept intake at zero forward speed (ground running conditions) is shown to be analogous to the flow round a sharp corner in a duct. Tests have been made on a model of a swept-wing leading-edge intake to ...
A simple method is described for calculating the spanwise loading over wing-fuselage combinations. It is based on Multhopp's method, which is extended here to cover wings of finite thickness, large root chords compared ...
The problem of predicting the rate of transport of a gas from or into the surface of a two-dimensional body in an airstream is discussed. The principal object of the investigation is to provide a means of estimating the ...
The stress concentrations are determined for a panel, bounded by main load-carrying members and an oblique edge, such as might occur at a cut-out in a swept wing. The solutions given are exact and cover the effects of a ...
A region of roughness, associated with the airflow conditions of the vortex-ring state, occurs when a helicopter is operating in vertical or near vertical descents in the range of about 500 and 1,500 ft/min. The turbulent ...
This paper is concerned with the formation of basic differential equations for the determination of the stress distribution in reinforced monocoque flat-sided structures, such as rectangular or polygonal fuselages and wing ...