The method of expressing the velocity increment over aerofoils directly in terms of the section ordinates (Refs. 1 and 2) is extended to cover also straight and swept wings of finite aspect ratio. The wings considered are ...
A method is developed for the calculation of the pressure distribution and the aerodynamic forces and moments acting on a wing at incidence, a wing in (steady) roll and a wing in (steady) pitch. The calculation is based ...
A simple method is described for calculating the pressure distribution on the surface of a thick two-dimensional aerofoil section, at any incidence, in incompressible potential flow. The method has been proposed by F. ...
Summary. The equation of motion for a flexible aircraft responding to a step gust is derived, and the relation developed between this and the response to an array of harmonic gusts. A Fourier transform method is used to ...
The problem of calculating the rotary lateral stability derivatives for a straight wing with a thin jet emerging at the trailing edge is considered. Based on Maskell and Spence's analysis of the effect of finite aspect ...
The results of some electric tank tests by Duquenne and Grandjean on wings of 45 deg sweepback with trailing edge flaps have been analysed to provide the basis for a method of calculating the spanwise loading. The analysis ...
Summary. In two-dimensional potential flow the combination of a source and a free vortex produces an axis-symmetric flow with streamlines in the form of equiangular spirals. Calculations have been made of the turbulent ...
J. H. B. Smith; J. A. Beasley; Diana Short; F. Walkden(1965)
According to the linearized theory of supersonic flow, both the local slope of the mean surface of a wing producing a specified distribution of lift and the pressure on a wing due to a specified distribution of volume are ...
A method of obtaining numerical values of generalised airforces on a thin wing oscillating harmonically in subsonic flow is described. It is assumed that the linearised equations of potential flow are valid. The essence ...
The whirling of shafts carrying rotors is a subject which has attracted the attention of many engineers and mathematicians notably Dunkerley, Chree, Stodola, Jeffcott and Morris during the past fifty years. The last ...
Two flat parallel surfaces, oscillating harmonically about a mean configuration are immersed in a uniform subsonic main stream in a direction parallel to the surfaces. The linearised equations of potential flow are assumed ...
The thin-jet model, applied by Spence to the study of the jet flap, is combined with the vortex-sheet model, applied by Mangler and Smith to the study of leading-edge separation, to study the effect of blowing from the ...
The thin jet model applied by Spence to the study of the jet flap is combined with the vortex sheet model applied by Mangler and Smith to the study of leading-edge separation, to study the effect of blowing from the ...
The vortex-sheet model of leading-edge separation previously applied to flat-plate delta wings has been applied to thick delta wings in the form of rhombic cones. The simplifications introduced by the use of slender-body ...
Detailed calculations are made of the flow over a series of bodies at Mach numbers of 1.2, 1.4 and 1.6 and Reynolds numbers of 48 to 72 millions. The bodies consist of a basic forebody and parallel portion to which are ...
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 ...
The influence of damping is examined by comparing the flutter critical speeds and frequencies obtained using the complete equations of motion and those obtained when all the damping terms are omitted. The calculations are ...
A calibration of the 8 ft x 8 ft wind tunnel has been performed at subsonic speeds using a multiple orifice, traversing, static pressure probe on the tunnel centreline. Full details have been obtained of the static pressure ...
Evidence from several check experiments indicated that the results of the preliminary calibration of 1935 were in error. The object of the described experiment was to investigate this and to calibrate the wind tunnel in ...