The objective of this work was to develop a method capable of producing reasonably accurate stage characteristics, in terms of mass flow, pressure ratio, work input and efficiency, for any centrifugal compressor with radial ...
The equations for helicopter performance are derived in a form suitable for the development of performance reduction methods, and the equations obtained provide also a simple method of performance estimation. Formulae are ...
The development of special smooth wing constructions for laminar-flow aerofoils calls for a simple testing technique to check the suitability of these new designs. In the method now used a short parallel length of wing ...
This report contains some fairly simple and economic methods for calculating the load distribution on wings of any plan form based on the conceptions of lifting-surface theory. The computer work required is only a small ...
The area-rule, moment of area-rule and transfer-rule methods for estimating the wave drag Of wing-body combinations are discussed. It is pointed out that the moment of area rule and the transfer rule are different forms ...
Methods recently developed for estimating distributions and intensities of sonic bangs are described. They are applied to several interesting flight manoeuvres and the results discussed in detail. The effect on sonic-bang ...
There is a great need for more accurate data on the aerodynamic derivatives of swept-back wings in order to solve problems of stability, control and flutter. As one step in the search for these data the estimation of the ...
Details are given of some of the methods of solving the flutter equations which have been programmed in Mercury Autocode at the R.A.E. Included is a method of following the variation of critical speed with a linear variation ...
PART I. Measurement of Tensile Strength. An experimental comparison has been made between five types of tensile tests including novel types designed to enable axial loading conditions to be approached more readily than is ...
The two-dimensional surface giving minimum pressure drag for given lift coefficient in supersonic flow is considered. The method adopted is a small perturbation of a plane surface; the pressure is expressed as a power ...