Summary. This report gives further experimental results for compressible turbulent boundary layers with air injection. The experimental arrangement is similar to that used by Jeromin (R. & M. 3526) but, by a slight ...
The wind-tunnel tests on cambered gothic wings reported in Reports and Memoranda No. 3211 have been extended to include the effects of changes in design lift coefficient and of changes in spanwise camber without changes ...
A comprehensive simulation of a slender-wing supersonic transport aircraft during approach and landing has been flown by a number of pilots from airlines and test establishments. The aim of the simulation was to obtain ...
An axially-symmetrical supersonic fully-expanded jet of diameter 0.75 in. was investigated by pitot- and static-tube traverses in the region from the exit to 100 diameters downstream. The investigation is supplementary to ...
The present work was undertaken in order to extend the existing experimental information on the 30 per cent. Griffith suction aerofoil obtained by Richards, Walker and Taylor (1945), in particular: (a) to investigate the ...
Compact devices attached to structures for the remote measurement of displacement and strain, utilising pneumatic principles, have potential advantage in long term creep-fatigue conditions, or at very elevated temperature. ...
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 ...
The effect of a flexible, geared, elevator tab upon the validity of the stiffness criteria for tail-units and rear fuselages is examined. To this end, the distortions of a hypothetical, semi-rigid tail-unit under the air ...
A general method (requiring the aid of a digital computer) is described for deriving the influence coefficients of any type of wing, and hence for evaluating its strength and stiffness characteristics. The method allows ...
Summary. A study of steady lift interference effects in wind tunnels with several different wall conditions has been carried out using a three-dimensional resistance network. The methods by which the various boundary ...
In this report an attempt is made to summarise the theoretical work carried out during the past few years aimed at discovering the potentialities of the gas turbine as a power plant in many fields of application, but ...
A general method of treatment of stick-fixed static longitudinal stability with propellers is given, distortion and compressibility effects being neglected. Model full-throttle data on some single-engined fighters are ...
The T-tail under investigation consists of a flat horizontal tailplane mounted on top of a flat vertical fin. The chords of the two surfaces at their junction are of the same length and are coincident. The T-tail is assumed ...
The flow of air past an infinite shell is considered. In its undisturbed state the shell is a circular cylinder. A portion of the shell between two normal cross-sections is flexible, the rest of the shell being rigid and ...
Three related methods are presented for calculating the skin friction and other characteristics in the laminar boundary layer on a non-adiabatic wall of constant temperature in the presence of pressure gradients. The first ...
The motion of an aircraft operating under perfect speed constraint (e.g. by an appropriate autothrottle) is examined theoretically and it is shown that, if engine thrust acts through the aircraft centre of gravity, the ...
This Report describes a new technique for finding automatically, when using multipoint excitation, the force distribution required to produce in-phase responses at the excitation points on a structure. It is shown how this ...
A graphical method, based on 'classical' flutter theory, is described which provides a simple test of the effectiveness of mass-balancing in the prevention of flutter at various heights. Illustrative applications are made ...
A recent study of velocity profiles in the turbulent boundary layer on a flat plate at high Mach numbers has suggested the formula for relating the form parameter H to its incompressible value Hi. This formula is used in ...
Part I. The report presents the theoretical calculations of gust alleviation factor made for rigid aircraft and with one degree of freedom only (i.e., vertical motion). It is shown that for average gust lengths and for ...