Normal classical theory is somewhat complicated for design use, and this report describes a simple method for the use. of designers : briefly, this is to estimate a straight-tapered wing equivalent to the'wing under ...
This note explains an improved numerical method of evaluating the contributions to the downwash at moderate or large spanwise distances from a vortex lattice. By allowing freedom of choice of ihe chordwise positions of the ...
Part 1. Details of the Mathematical Techniques used in the Evaluation of the Pressure Distributions, and a Set of Numerical Results including Comparisons with Experiment. Details of a method which enables the calculation ...
The problem of predicting the rate of transport of a gas from or into the surface of a two-dimensional body in an airstream is discussed. The principal object of the investigation is to provide a means of estimating the ...
An analysis has been made of the processes which follow when a drop of liquid is subjected to a sudden change in the condition of the air in which it is suspended. Equations are given from which either the temperature of ...
No hitherto successful attempts except one (by Griffith and Meredith) have been made to provide an exact solution of the boundary-layer equations of motion when there is a continuous normal velocity at the boundary. At the ...
A method for calculating the incompressible potential flow about two particular aerofoil sections is presented. The potential flow about two lifting circles is calculated by the method of images, and the two circles are ...
The design of axial-flow turbines has been hampered in the past by a lack of comprehensive data regarding pressure losses and gas deflections through rows of turbine blades. In the present report much of the available ...
It is demonstrated in this report that the 'steady stick force per g' as defined by Gates and Lyon in R. & M. 2027 is the best criterion for the measurement of manoeuvrability of an aircraft because: (a) practically, it ...
Calculations of the pressure on a flat elliptic cone and on a flat elliptic hyper-cone at supersonic speeds and zero incidence are made for the case when the cones lie inside the Mach cone of the apex. The results are ...