The downwash induced by planar vorticity distributions has been computed by exact linear theory and by the R.A.E. Standard Method to examine the accuracy of the approximate method. The results on wings of infinite span ...
An experimental investigation has been made of the subsonic lift, drag and longitudinal stability characteristics of models representing some alternative slender airbus configurations. For the same wing planform of aspect ...
Two flat parallel surfaces, oscillating harmonically about a mean configuration are immersed in a uniform subsonic main stream in a direction parallel to the surfaces. The linearised equations of potential flow are assumed ...
This paper lists one hundred titles which have been published in the R. & M. Series of the Aeronautical Research Council. The Council number is included for the purpose of record only.
The singular double integrals which arise in the calculation of the components of perturbation velocity due to a swept wing with given thickness distribution by linearised theory, have been evaluated by a numerical method. ...
This Report describes an analysis of air resonance in the hover, and the solutions obtained for a helicopter with non-articulated blades. It is shown that stability in air resonance depends critically on blade structural ...
The flow physics for inviscid flow on an arbitrary two-dimensional streamsurface for application to turbo-machines are re-examined without specialising to a particular type of surface. This re-examination introduces ...
The oscillatory behaviour of a T-tail has been investigated at high subsonic Mach numbers on an aeroelastic model having tailplane settings of zero and three degrees. There is broadly satisfactory agreement between calculated ...
Summary.--The general method of Pohlhausen, which is discussed in detail in Ref. 1, uses a uniparametric system of velocity distributions of the form u/U = f(y/delta) + lamda.g(y/delta). Pohlhausen, by choosing simple forms ...
Measurements of lift, drag and pitching moment have been made on a series of cropped delta wings of aspect ratio 1.4, 1.2, 1.0 and 0.8 formed by successively cropping a delta-wing model of aspect ratio 1.6. These tests ...
A calculation method has been developed which uses the compressible forms of the boundary-layer momentum integral and entrainment equations in a general, curvilinear surface coordinate system in which the axes are not ...
Some leaded windows have been subjected to a series of sonic bang response tests using a specially developed explosive simulated bang. The tests covered a range of bang pressures and durations. Results show that the ...
Results are presented of a study of the pressures on the flat windward surfaces of two wings with curved, sharp leading edges. The leading edges of one of the wings are convex outwards, whereas those of the second are ...
The steady laminar incompressible boundary-layer problem in two dimensions has been posed as an integral equation in Crocco variables in the most general case and an algorithm developed for computing the similarity flows ...
A detailed comparison of resu[ts has been made from several series of flight tests, spanning a number of years, on the Fairey Delta 2, with wind tunnel tests on 1/9 and 1/24 scale models and with reference also to simple ...
At St. David's Cathedral, structural vibrations produced by a number of Concorde sonic bangs have been measured and compared with the vibration produced by the structures normal environment. The results show that bang ...
An approximate theoretical formula for the distribution of aerodynamic load over arbitrary thick wings in incompressible flow is developed by combining three-dimensional results from thin-wing theory with twodimensional ...
In this report, the Kron eigenvalue procedure is established by the application of Hamilton's principle to a constrained primitive Lagrangian, comprising the characteristics of the various sub-systems into which a composite ...
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 following investigation formed part of a more general research on problems associated with high-lift flaps. To obtain the maximum advantage from such devices, a satisfactory alternative to the conventional aileron is ...