Theoretical investigations have been made of the flutter of an idealised trimming tab system having three degrees of freedom - normal translation of the main lifting surface, rotation of the control surface and rotation ...
A method is derived for calculating the spanwise load distribution over a lifting wing having a long circular-cylindrical body at one end. The solution is derived for arrangements giving constant induced downwash, but can ...
The spanwise load distribution is calculated for wings with plates normal to the wing and parallel to the main stream, or inclined to it at a small angle. The calculations are made for configurations having minimum induced ...
A theory has been developed for calculating the distributions of sideforce and lift on fin-fuselage-tailplane arrangements in a side-wind but with the tailplane set at zero incidence. The analysis is limited to incompressible ...
By means of Relf's analogy between aerodynamic streamline flow and electric potential flow, the theoretical pressure distributions around a series of conventional turbine blades in cascade have been determined over a range ...
The need of using stability derivatives of unsteady.(oscillatory) motion is explained, and requirements of tunnel experiments for determining them are established. These are based on simple theoretical considerations, valid ...
This paper is concerned with the design of annular supersonic nozzles to produce uniform flow in supersonic wind tunnels which are axi-symmetrical and which have an internal coaxial circular cylinder throughout. Symmetrical ...
During the final landing approach pilots are often observed to attempt tight control of flight path by coarse elevator usage. It is shown by theoretical analysis that this form of control is inherently conducive to instability ...
The report describes a theoretical investigation in support of measurements being made on an oscillating half-wing model of the plan-form shown in Fig. 1 in the National Physical Laboratory 25 in. by 20 in. Wind Tunnel ...
The drag of a non-lifting swept wing of infinite span is investigated for supersonic flow when the Mach lines from the wing apex lie ahead of the wing leading-edge. The wing section is assumed to be arbitrary but identical ...
The effectiveness of a beam-riding missile is greatly influenced by the mutual effect of noise and nonlinearities. The former is mostly due to radar jitter, while the principal non-linearity is that introduced by limiting ...
To first order in frequency, subsonic lifting-surface theory is applied to arbitrary configurations of a thin wing and a trailing-edge control. The discontinuities in flow direction at the hinge line and part-span boundaries ...
In parallel with a recent experimental study of the use of slotted tunnel liners with variable perforated screens to give interference-free aerodynamic damping derivatives, the corresponding problem is considered theoretically. ...
By an arithmetical method, contours of constant Mach number have been determined in the contraction cone of a circular tunnel whose axial distribution of area was assumed to be the same as that in the Royal Aircraft ...
This report investigates the wave drag of bodies of revolution with pointed or open-nose forebodies and pointed or truncated afterbodies. The 'quasi-cylinder' and 'slender-body' theories are reviewed, a reversibility theorem ...
In special circumstances where a large work output is required from a turbine in a single stage it is necessary to us e high pressure ratios across the nozzle blades, thus producing supersonic velocities at inlet to the ...
A mathematical theory of aerofoil spoilers in two-dimensional subsonic flow is presented. Equations are given for load distributions, lift, drag, moments and hinge moments pro.duced by spoiler-flap combinations. The theory ...
Spoilers, split flaps and sometimes (with thin aerofoils) incidence alone cause the flow to separate from the aerofoil surface. This flow often reattaches to form a closed bubble of virtually stationary air at a fairly ...
Summary. Experiment has already shown that the aerodynamic damping on half-span models in pitching oscillation is subject to interference effects that may exceed 30 per cent in slotted-wall tunnels at subsonic speeds. An ...
Summary. This Report gives a description of an extension to wings oscillating at general frequencies of Multhopp\\'s lifting-surface theory for wings in steady subsonic flow. This particular variant of the \\'kernel ...