The stability of an annular air intake at a Mach number of 1.4 and with Reynolds numbers of about 1.5 x 10power6 is considered in detail and a method is described whereby the experimental results might be extrapolated for ...
The formation of a conical shock and a conical region of flow separation originating from the tip of a thin traversing tube was observed in a supersonic tunnel as a result of interaction of a strong shock with the boundary ...
Several methods of constructing contra-flow turbo-compiessor wheels have been investigated by mechanical tests on single-stage wheels. The results have been incorporated in a complete unit which has been designed and tested ...
The problem of calculating the response of an aircraft in rolling manoeuvres when the mass distribution of the aircraft is such that the inertia terms in the equations of motion effect a cross-coupling of the usual lateral ...
A semi-automatic data handling system has been constructed at the R.A.E. for use in wind tunnel and laboratory tests on aeroelastic models. The system can accept fifty inputs of static information and fifty oscillatory ...
Summary. The theory is developed for the control characteristics of aircraft in which direct lift is commanded directly by the pilots\\' stick. Basic requirements are established for acceptable response characteristics; ...
Control effectiveness tests, using the ground-launched rocket-boosted model technique, have been made on rectangular wings of aspect ratio 4, EC.1250 section, and fitted with a 25 per cent chord concave control flap. Tests ...
A method is described of controlling the phase of the free motion of control surfaces by viscous friction and geared masses. Substantial improvements in the damping of aircraft oscillations can be achieved if such devices ...
If ad hoc wind-tunnel work on controls is to be of value it is essential that the same precautions should be taken as are necessary for fundamental research. For the model there must be careful selection of material and ...
The term buzz, as used here, refers to a class of control-surface oscillations sometimes encountered during flight at transonic or low supersonic speeds. Essentially these are self-excited oscillations in, a single degree ...
The determination of the stick-free flutter characteristics of a control system when the inertia of the stick is allowed for is considered. A method of solution is proposed which corresponds to impedance matching between ...
Summary. It is shown that an increase of Mach number from approximately 0.2 to 0.4 at entry to a convergent nozzle of specified shape does not appreciably change its performance. Such a nozzle is thus recommended as a ...
The recent increase in the speed of aeroplanes has brought the question of cooling drag into prominence and forced the application of the principle of low velocity cooling. An analysis of the performance of a cooling system ...