A new closed loop system is described which enables the incidence, roll and motivator (i.e. control surface) angles of a wind tunnel model to be controlled remotely, either by hand or by analogue voltages derived from, ...
The combination of two universal functions, representing the effects of the wall and of the 'intermittency' in the other region, has been used to construct a new profile family. Comparisons with measured profiles are very ...
Tests were made on a 1/2.25 scale model of a half wing of the Master. The span of the aileron was 0.22s and the chords were 0.2c and 0.15c; the aileron was fitted with a balance tab of 0.05c chord. Measurements were made ...
Summary. An extensive model-test programme has been carried out on the noise properties of a series of fifteen axi-symmetric ejectors, using a two-inch diameter cold jet as the primary discharge and inducing the secondary ...
The vortex-sheet model of leading-edge separation which has been successfully applied to slender delta wings of conical shape is extended to non-conical wings which have thin, uncambered cross-sections. Calculations of the ...
Non-linear oscillatory-motion histories, measured in the R.A.E. wind-tunnel/flight-dynamics simulator, are analysed. The resulting dynamic-motion characteristics for large-amplitude motions in the pitch plane are discussed ...
Leading-edge separation from fairly thin wings of moderate or low aspect ratio gives rise to aerodynamic loading and forces that are non-linear with incidence. It is important to be able to estimate these effects theoretically ...
This paper is concerned with the classification of nonlinear vibration problems which occur in the field of aeronautics - excluding those problems which may be more suitably defined under the heading 'nonlinear problems ...