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. ...
Ground clearance requirements are considered in relation to take-off, treating lift-off as a dynamic manoeuvre. It is shown that ground clearance is defined by conditions about one to two seconds after lift-off. Simple ...
An integrated analytical treatment is presented which deals with the equilibrium and stability of the flexible aeroplane in flight. The analysis embodies those methods currently employed to investigate the behaviour of the ...
As an aid to discussions on the future provision of meteorological forecasting services for civil transport operations, an approximate assessment is made of the effects of changes in the accuracy with which en-route and ...
Mean pressure recovery, distortion and the extent of stable subcritical flow have been measured at zero incidence on a fuselage side intake having a wedge compression surface. The intake was separated from the fuselage by ...
This Report describes an experimental investigation of the factors affecting the base flow and jet structure behind a cylindrical after-body with a central nozzle. Seven interchangeable nozzles were tested. Six of these ...
One possible method of reducing jet noise at take-off is the use of an ejector in which the propelling nozzle discharges into a shroud and thereby induces a secondary flow. The present report describes an experiment on the ...