Aeronautical Research Council (1945-1979): Recent submissions

Now showing items 21-40 of 2706

The theory of interference effects on dynamic measurements in slotted-wall tunnels at subsonic speeds and comparisons with Experiment

H. C. Garner; A. W. Moore; K. C. Wight (1966)

Summary. Experiment has already shown that the aerodynamic damping on half-span models in pitching oscillation is subject to interference effects that may exceed 30 per cent in slotted-wall tunnels at subsonic speeds. An ...
Measurements of skin friction on a cambered delta wing at supersonic speeds

K. G. Winter; K. G. Smith (1965)

Summary. The measurements, using razor blade surface pitot tubes, show that the relatively mild pressure gradients and streamline convergence on the wing have a large effect on local skin friction. Application of the ...
The flow produced by interaction of a turbulent boundary layer with a normal shock wave of strength sufficient to cause separation

J. Seddon (1960)

Summary. The nature of normal-shock and turbulent-boundary-layer interaction is described on the basis of an experiment involving two-dimensional flow, at M = 1.47, over a flat plate. Special attention is paid to the flow ...
The high-speed laboratory of the aerodynamics Division, N.P.L. Part I - description of the installation. Part II - experimental techniques. Part III - experimental results.

D. W. Holder (1946)

The first part of this report describes the Ngh-speed tunnel installation in the Aerodynamics Division of the National Physical Laboratory. The installation consists of the 12-in. diameter High-Speed Tunnel, the 20 x 8-in. ...
Low-speed measurements of skin-friction on a slender wing

L. A. Wyatt; L. F. East (1966)

Summary. Extensive measurements have been made with surface pitot-tubes of the skin friction on the upper surface of a slender wing. The surface pitot-tubes took the form of razor-blade segments attached magnetically to ...
Calculation of the response of a flexible aircraft to harmonic and discrete gusts by a transform method

C. G. B. Mitchell (1965)

Summary. The equation of motion for a flexible aircraft responding to a step gust is derived, and the relation developed between this and the response to an array of harmonic gusts. A Fourier transform method is used to ...
Wind tunnel tests on a nacelle fitted with two lifting fans in tandem

N. Gregory; Edna M. Love (1966)

Summary. Results are given of wind-tunnel tests of a nacelle-shaped body fitted with two lifting fans in tandem. Lift, drag and pitching moment were measured both with the fans installed with axes vertical and also in a ...
The subcritical response and flutter of a swept-wing model

C. A. K. Irwin; P. R. Guyett (1965)

Summary. The dampings and frequencies of the lower natural modes of oscillation of an aeroelastic, swept-wing model at wind speeds below its critical flutter speed have been deduced from measurements of the displacement-vector ...
An electronic analogue computer representing twelve coupled linear differential equations

W. D. Hicks (1965)

Summary. This paper describes the design, construction and operation of an electronic network providing an analogue of the behaviour of up to twelve coupled, second-order, linear differential equations. It was designed ...
Some calculations of the take-off behaviour of a slender-wing supersonic transport design constrained to follow a specified pitch-attitude time history

B. N. Tomlinson; M. Judd (1965)

Summary. The rotation and flare-up phases of the take-off of a slender-wing supersonic transport aircraft are studied by calculating the time histories of speed, height, etc. when the pitch-attitude time history is specified. ...
The radiation sound field of a rectangular panel set in an infinite wall and excited by a turbulent boundary layer

D. E. Davies (1964)

A flexible panel, set in the an infinite wall, is subject to an excitation force distribution which can be described by a correlation function. The panel vibrates and radiates sound. Expressions are derived for the intensity ...
Design and test of a series of annular aerofoils

D. L. Ryall; I. F. Collins (1965)

The results of a series of wind tunnel tests involving velocity, surface pressure and force measurements on six annular aerofoils are presented together with details of the design procedure which was based on that given ...
Comparative numerical applications of the reverse-flow theorem to oscillating wings and control surfaces

Doris E. Lehrian; H. C. Garner (1965)

The reverse-flow theorem gives alternative integrals for generalized forces on oscillating wings by linearized theory. Applications to analytical and numerical solutions are discussed, and the latter are considered in some ...
Some early experiments on vortex separation

P. T. Fink; J. Taylor (1966)

Part I. Some Low Speed Aerodynamic Properties of Cones. The results are presented of some low-speed wind tunnel tests on a right circular cone with apex angle 20 deg. and on elliptic cones with apex angles 60 deg. and 20 ...
The measurement of skin friction in supersonic flow by means of heated thin film gauges

B. J. Bellhouse; D. L. Schultz (1965)

The application of heated thin film gauges to the measurement of mean skin friction in compressible flow is described. It is shown that the calibration of the gauges is independent of Mach number, at least up to M = 3, ...
Influence of Tuned Dampers on Flexure-Aileron Flutter. Parts I-III.

R.A. Frazer et al (1946)

Part I - Theoretical Investigation on the Influence of Tuned Damping Devices on Flexure-Aileron Flutter. Part II - Some Further Calculations on the Influence of Tuned Damping Devices on Flexure-Aileron Flutter. Part III - ...
Flight measurements of the elevator and aileron hinge-moment derivatives of the Fairey Delta 2 aircraft up to a Mach number of 1.6 and comparisons with wind-tunnel results

R. Rose; O. P. Nicholas; Glynis Vorley (1965)

Aileron and elevator hinge-moment derivatives have been extracted from flight tests on the Fairey Delta 2 in which the dynamic aircraft response, to control pulses was recorded. As this method is not widely used, and has ...
Leakage and secondary flows i compressor cascades

B. Lakshminarayana; J. H. Horlock (1965)

This paper describes the effects of leakage and secondary flows on lift, outlet angles, induced drag and loss coefficients in a rectilinear cascade of compressor blades in which spanwise gaps simulated the clearance spaces ...
The transonic flow in the throat region of a two-dimensional nozzle with walls of arbitrary smooth profile

A. W. Moore (1965)

A solution is presented for the flow in the throat region of a two-dimensional nozzle with an arbitrary smooth profile. The velocity components are determined as series expansions in ascending powers of Rpower-0.5 where R ...
Temperature and pressure studies in the reservoir of a reflected-shock hypersonic tunnel

K. C. Lapworth; J. E. G. Townsend (1964)

Temperatures and pressures have been measured in the shock-heated gas upstream of the nozzle of a reflected-shock hypersonic tunnel. Temperatures were measured by spectrum-line reversal, using sodium D lines for some ...

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