The vortex-lattice method of calculating flutter derivatives presented in this note is an extension to higher frequencies of the work on stability derivatives reported in R. & M. 2922. The method is a modified form of the ...
A numerical method of solving the integral equation connecting the lift and downwash on a wing oscillating harmonically in a supersonic flow of any Mach number is described. The integral equation is replaced by a matrix ...
Comparisons are made between low-speed experimental results and estimates based on attached-flow theory for the lateral stability derivatives of slender wings at incidence, and it is found that the flow separation has ...
The need to know two-dimensional low-speed characteristics accurately in designing swept-back wings for transonic aircraft has led to a revival of interest in calculations of the loss of lift below the ideal-flow value ...
The purpose of this paper is to fred a sound approach to the problem of the theoretical prediction of sectional characteristics taking account of the boundary layer. Attention is mainly concentrated on the lift, since it ...
A method of calculating stability derivatives for wings oscillating at low frequencies is developed from the modified vortex-lattice method outlined in R. & M. 2470. Derivatives are obtained for the following wings describing ...
The aerodynamic loading is formulated for a family of symmetrically tapered wings describing simple harmonic pitching oscillations of low frequency in supersonic flow. The planforms have supersonic leading and trailing ...
Summary. An oscillatory lifting-surface theory for subsonic flow (Ref. 1) is used to calculate the aerodynamic forces on an oscillating arrowhead wing of aspect ratio 2 with trailing-edge control surfaces of varying span. ...
A calculation of the complete downwash in three dimensions due to a rectangular vortex, is given for the limited range Z = ± 4. The downwash is computed at selected positions, in planes normal to the plane of the vortex; ...
Several methods are available for the calculation of the compressible turbulent boundary-layer. The earlier methods of Tucker (1951) and Young (1953) involve numerical integration, while the more recent methods of Englert ...
So far, little is known of the effect of camber or twist on the pressure distribution and drag of a wing flying at supersonic speeds, but with subsonic leading edges. According to the linear theory, for a subsonic leading ...
The lift distribution along a wing of infinite span with a central jet of higher velocity is calculated by standard methods of aerofoil theory for several values of (jet velocity/stream velocity) and of (jet diameter/wing ...
Computer programs have been written to evaluate the integrals of lifting-surface theory for the velocity field of a thin wing with given load distribution. Different programs are used for the downwash at points on the wing, ...
From systematic three-component measurements of wing-body combinations with swept wings it has been found that the movement of the aerodynamic centre due to the influence of the body is greater for a swept forward than for ...
Using distributions of vortices and sources over the aerofoil surface, approximate formulae are developed for finding the spanwise and chordwise loadings of cranked wings (i.e., wings with discontinuous changes of sweep), ...
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 ...