A method of calculating the tunnel interference due to oscillating loadings on wings in rectangular tunnels is described. This will apply to incompressible flow for all frequencies or to subsonic flow for small frequencies. ...

The design of a turbine stage is considered on the basis of free vortex flow from the nozzles and blades and some of the factors which limit the design of an efficient turbine stage are discussed. As the flow conditions ...

Some oscillatory aerodynamic derivatives for wing pitch and translation, and control-surface rotation have been found from measurements in a low-speed wind tunnel. The wing was a modified cropped delta of biconvex circular-arc ...

Pressure-plotting and strain-gauge balance tests have been made at a Mach number of 1.41 on a conically cambered cone of 30° semi-vertex angle, and with a ratio of the major to the minor axis of its cross-section equal to ...

The lift distribution on a two-dimensional wing oscillating in accelerated flight is obtained by solving the linearised partial differential equation for the velocity potential in the fluid flow about the wing and applying ...

Part I. Two methods are derived for calculating the heat transfer through a constant-property laminar boundary layer, that depend respectively on approximations valid at low and high values of σ, the Prandtl number. The ...

In this report are given some of the methods used in three-dimensional subsonic flutter-derivative theory. It is hoped that it will provide a basis for the reading of specific papers on the subject. Two proofs are given ...

The main object of this report is to describe and illustrate a fairly simple exact method by which aerofoils and other surfaces may be constructed to have desired velocity distributions. Its subsidiary interest is as a ...

Summary.--In this report the results are given of an investigation, without the application of suction, into the lift, drag and pitching moment of an aerofoil of 31.5 per cent thickness/chord ratio designed specifically ...

An analysis is presented of the buckling of the leading edge of a thin built-up wing subjected to spanwise thermal stress. Computed values of the buckling load are given in graphical form for a wide variation of leading-edge ...