A calculation method is described for unsteady, subsonic flow through an infinite, two-dimensional cascade of flat plate blades at zero mean incidence. The unsteady blade lift and moment, generated acoustic waves and shed ...
The report describes experiments devised to investigate some of the previously unexplained peculiarities of normal types of pitot-static tube. Revised basic calibration factors for various instruments are recorded. In the ...
Some of the characteristics of jet-lift V/STOL aircraft are discussed in terms of their effect on the ability of these aircraft to operate from small, semi-prepared sites, without the usual airfield facilities, in both ...
The paper presents a review of recent experimental and theoretical research on two-dimensional base flows. The main object is to illustrate the extent to which the basic properties of the flow are understood in each of the ...
The function of the manometer is to enable small pressure differences to be measured at a distance. The instrument will measure either the difference of two pressures or a single pressure relative to atmosphere. The accurate ...
Some measurements of downwash have been made in a plane behind a 12-ft diameter helicopter rotor over a range of shaft inclination and tip speed ratio. In the various operating conditions, the tunnel tests are in reasonable ...
The drag increase beyond the critical Mach number is calculated by modifying the supersonic part of the Karman-Tsien pressure distribution on a profile. This is possible when the supersonic regions are not too large. The ...
The drag of an infinite swept wing is found in terms of the drag of a related unswept wing having the same relative position of transition. Results in incompressible flow are expressed in terms of a 'sweep factor'. Detailed ...
Camber and twist is applied to the problem of reducing the drag due to incidence, of thin triangular or swept-back wings, at supersonic speeds, with subsonic leading edges and supersonic or sonic trailing edges. Two cases ...
An account is given of a full-scale investigation into the stresses occurring in the wing members of a Sunderland flying boat during landing impacts. It is found that the main dynamic effect is caused by the wing oscillating ...
Flight measurements have been made of the phugoid motion of the Hoverfly Mk. I helicopter, following an arbitrary longitudinal displacement of the control, the latter being returned to its initial position and held fixed. ...