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 ...
An analysis of aircraft response and loading conditions in symmetrical manoeuvres is presented with a particular recognition of the designer's needs. The analysis is based on the theory of aircraft response to elevator ...
The velocity distribution around the nose of an NACA 0015-64 aerofoil was found by experiment and that around the nose of a Piercy 15/40 aerofoil by calculation for various angles of incidence and flap deflection. It was ...
The problems of engine airflow representation in wind-tunnel models are reviewed. Methods which have been used satisfactorily in low subsonic tunnels are described briefly. Special difficulties associated with testing at ...
When aerodynamic coefficients are calculated for tailplane flutter calculations it is usual to neglect the aerodynamic effect on the tailplane of the disturbance due to the wing and to assume that the tailplane oscillates ...
The results of some electric tank tests by Duquenne and Grandjean on wings of 45 deg sweepback with trailing edge flaps have been analysed to provide the basis for a method of calculating the spanwise loading. The analysis ...
The boundary-layer equations are derived for a very general co-ordinate system, and various theorems hitherto only proved in more restrictive systems are extended to this general system. The particular case of streamlines ...
Relationships have been derived for expressing the velocities on three-dimensional tapered wings at zero incidence in terms of the velocities on untapered infinite swept wings. The theoretical investigation of the effects ...
An approximate method of estimating the effect of the ground on the lift of a rotor at any forward speed is described. Flight tests on several different helicopters show reasonable agreement with the theory. Curves are ...
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 ...
Estimates of atmospheric turbulence from counting accelerometer records show a large scatter. The simple assumption of a random distribution of gusts is inconsistent with this scatter. A formula which takes account of the ...
An experimental study has been made of two-dimensional turbulent boundary-layer flow with zero pressure gradient. The investigation was made to determine the accuracy of a method proposed by Preston for measuring the local ...
This paper gives the results of an investigation into the effects of wing torsion in a ternary-type spring tab flutter. The results presented are for a series of calculations on an idealised system having degrees of freedom ...
This report investigates the extent to which the dynamic behaviour of a torpedo is sensitive to changes in its stability derivatives. The main object in carrying out the investigation was to provide guidance on the accuracy ...
An analysis has been made of the full-scale measured drag and lift performance, data available on the Sunderland, Solent, Shetland, Sealand, Saro E.6/44 and Princess boat seaplanes, which all have hulls of fairly orthodox ...
Wind-tunnel test results for the flutter of a swept-back wing carrying a localised mass, and having symmetric or antisymmetric freedoms of the root, are given. The tests were made on a model wing of 23 deg sweepback, the ...
The incompressible flow past an aerofoil with a thin jet emerging from its lower surface somewhere near the trailing edge is considered. Based on unpublished work of Gates, Maskell and Spence, a simple method is described ...
The paper describes an investigation of the effect of structural damping in the torsion mode on wing flutter with the object of finding circumstances in which damping reduces the flutter speed. The drop in flutter speed ...
Tests have been made on a series of high length/beam ratio seaplane hulls with high beam loadings. The effects of varying the hull parameters, forebody warp, afterbody length and afterbody angle, together with the interaction ...
A criterion is given for the convergence of numerical solutions of the Navier-Stokes equations in two dimensions under steady conditions. The criterion applies to all cases, of steady viscous flow in two dimensions and ...