Five methods for the approximate solution of the momentum integral equations for the three dimensional turbulent boundary layer are presented. These include the removal of the usual small cross-flow velocity restriction ...
The object of a blade-to-blade method is to calculate the blade surface velocity distribution and the outlet angle for a given three-dimensional cascade. These give the heat drop or work done and indicate whether shock ...
Summary.--The lift, pitching moment and hinge moment are derived for a delta wing with a trailing-edge flap of constant chord when tile wing is at zero incidence in a supersonic air stream and tile flap oscillates harmonically ...
Summary.--The lift, pitching moment and full-span constant-chord control hinge-moment are derived for a cropped delta wing describing harmonic plunging and pitching oscillations of small amplitude and low-frequency parameter ...
This report describes an application of a digital computer to the aerodynamic design and automatic control of a large wind tunnel with flexible walls. The computational problem was threefold : first, calculation of the ...
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), ...