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 ...