A method is presented of analysing experimental curves obtained in flight when an aircraft is disturbed longitudinally by a suitable elevator input and performs mainly short-period oscillations. Determination of frequency, ...
S. Neumark; J. Collingbourne; H. H. B. M. Thomas(1954)
Following flight experience of a particular aircraft, the effect of including a bob-weight and feel spring in the circuit of a power-operated longitudinal control on the dynamic stability of the aircraft is investigated. ...
The concept of complex stiffness in problems of oscillations with viscous, or structural (hysteretic) damping is often used in a wrong way, leading to erroneous solutions. It is shown in the Paper that correct expressions ...
In this paper, which is a continuation of two earlier ones (R. & M.'s 2713 & 2717), the subsonic flow past untapered swept wings, at zero incidence, is further investigated using linear theory. Methods for calculating ...
The theory of equilibrium of balloon flying cables is presented in a simplified form most suitable for applications, with numerical tables covering probably the full range of practical cases. A simplified derivation of ...
This paper contains an attempt to explain the incremental negative or positive lift induced on an aerofoil by an external non-lifting body (such as an engine nacelle), as observed in some experiments. A two-dimensional ...
The paper presents systematic tables of formulae whose purpose is to facilitate the operational solution of response problems reducible to linear differential equations with constant coefficients and with simple forcing ...
Practical difficulties in cruising below minimum drag speed have long been known but not fully explained. The reasoning proposed by Painleve in 1910 purported that flight below minimum drag speed should be fundamentally ...
A method, alternative to that in common use at present, of calculating the response quantities in pull-out manoeuvres relevant to important cases of loads and stresses in aeroplane structures, is presented. The method, ...
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 ...
An attempt is made to clarify the position as to the comparative two-dimensional velocity distributions on a thin doubly symmetrical aerofoil and on the corresponding semi-infinite body, the front part being the same in ...
A solution by H. Ludwieg, giving the velocity distribution in tile central section of a thin swept-back wing of infinite aspect ratio with a biconvex profile at zero incidence, has been found erroneous. In connection with ...
A new method of determining velocity distribution on slender bodies of revolution in axial flow is expounded, analogous to the linear perturbation method widely used for slender symmetrical profiles in two dimensions. The ...
This report is a continuation of four earlier ones by the present authors and contains a theoretical investigation of subsonic flow past thin tapered swept-back wings at zero incidence, by the first-order method. The basic ...
This report is a continuation of three earlier ones by the present authors (1947-9) and contains a theoretical investigation of subsonic flow past thin tapered unswept wings (of full or cropped-rhombus plan form), at zero ...