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Now showing items 1262-1281 of 1313

Wall corrections for wings oscillating in wind tunnels of closed rectangular section. Part I Theory and Tables. Part II Applications to a Delta Planform in a 9 x 7 Tunnel

W. E. A. Acum (1958)

A method of calculating the tunnel interference due to oscillating loadings on wings in rectangular tunnels is described. This will apply to incompressible flow for all frequencies or to subsonic flow for small frequencies. ...
Water and air performance of seaplane hulls as affected by fairing and fineness ratio

A. G. Smith; J. E. Allen (1950)

An analysis is made of data on the variation of hull air drag with length/beam ratio and degree of local fairing, and of the maximum beam loading permitted for reasonable hydrodynamic performance. The effect of length/beam ...
Water performance of a four-engined flying boat with step fairings of length 3, 6 and 9 times the step depth

G. J. Evans; A. G. Smith; R. A. Shaw; W. Morris (1941)

Tests were made to investigate the hydrodynamic qualities of the Sunderland flying boat, when fitted with step fairings of mean gradient 1 : 3, 1 : 6 and 1 : 9. Attitude and acce]eration measurements were made during ...
The wave drag of non-lifting combinations of thin wings and 'non-slender' bodies

L. M. Sheppard (1957)

The methods of wave-drag estimation known as the area rule and transfer rule are restricted to non-lifting combinations of thin wings and slender bodies. The Lomax-Heaslet multipole method is applicable to configurations ...
Wave theory of the Mach-Zehnder interferometer

H. K. Zienkiewicz (1959)

A theory of the Mach-Zehnder interferometer is developed using the approach of investigating the history of a wave front produced by an element of an extended light source. Account is taken of the effects of imperfections ...
Weight optimization with flutter constraints

L. T. Niblett (1977)

It is argued that the formulation of the method of applying a flutter constraint in weight optimisation which allows for all the methods of avoiding flutter is so complicated that it is best not to try to include a flutter ...
Whirl of an Aircraft Power-plant Installation and its Interaction with the Flutter Motion of a Flexible Wing

G. E. Smith (1966)

Results of propeller whirl analyses in four degrees of freedom are presented for a typical turbo-prop aircraft power-plant installation consisting of a rigid engine supported with elastically restrained freedoms in pitch ...
A wind tunnel investigation of the longitudinal and lateral aerodynamic characteristics of a Canard Aircraft model Part 1 Tests at M = 1.04 and M = 2.02 Part 2 Tests at M = 2.47

P. E. Watts; L. J. Beecham; D. A. Treadgold (1959)

PART I. Tests were made in the Royal Aircraft Establishment No. 19 (18 in. x 18 in.) supersonic wind tunnel to measure the overall normal and side forces, rolling, pitching and yawing moments on a typical canard aircraft ...
Wind tunnel measurements of the low speed stalling characteristics of a model of the hawker-siddeley trident 1C

D. Isaacs (1968)

Under review
Wind tunnel studies of leading edge separation phenomena on a quarter-scale model of the outer panel of the handley page "Victor" wing, with and without nose droop

R. A. Wallis (1965)

Leading edge flows, present in the incidence range embracing the onset of general nose separation, have been studied experimentally. The effect of nose droop of these flows was established during the development of this ...
Wind tunnel tests and theoretical investigations on the effect of a localised mass on the flutter of a delta wing with fixed root

G. F. Donno (1959)

Summary.--Wind tunnel tests and theoretical investigations have been carried out to study the effect of a localised mass on the flutter characteristics of a delta wing. The experimental work covered a wide range of spanwise ...
Wind tunnel tests of a wing fitted with a single lifting fan

N. Gregory; W. G. Raymer; Edna M. Love (1964)

Results are given of wind-tunnel tests of a square wing with a lifting fan of 1/44th the wing area located at 0.354 chord. Forces and pressure distributions were measured both on the bare wing and with plain and split ...
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 ...
Wind Tunnel Tests on a Streamlined Fan-Lift Nacelle Part I. Tests on Nacelle Alone and with Wings or Underfins Fitted Part II. The effect of Forward Speed on the Lift Produced by a Lifting Fan and its Inlet

J. E. Hackett (1965)

Part I describes tests on a streamlined body with a lifting fan mounted normally to its axis. Most of the tests were made in the 5 ft x 4 ft windtunnel at Imperial College, and others in the No. 1 11½ ft x 8½ ft tunnel at ...
Wind tunnel tests on cambered wings of mild gothic planform part 1 further low-speed tests part 2 transonic tests

P.J. Butterworth; P. Lee (1977)

Measurements are reported of the longitudinal characteristics of seven wings of mild gothic planform, aspect ratio 1.4, sharp leading edges, and two different thickness ratios. Five of these were cambered to keep the flow ...
Wind-tunnel experiments on a rectangular-wing jet-flap model of aspect-ratio 6

A. J. Alexander; J. Williams (1961)

Balance measurements of lift, pitching moment and thrust on an aspect-ratio 6 half-model wing and body in the N.P.L. 13 ft × 9 ft Wind Tunnel are discussed, and compared with theoretical estimates. The experimental ...
Wind-Tunnel Experiments on the Flow over Rectangular Cavities at Subsonic and Transonic Speeds

J. E. Rossiter (1964)

Measurements have been made of the time average and unsteady pressures acting on the roof and behind a series of rectangular cavities set in the roof of the 2 ft x 1 1/2 ft transonic tunnel. It was found that the unsteady ...
Wind-tunnel experiments on the squidding of parachutes

L. F. G. Simmons; R. W. F. Gould; C. F. Cowdrey (1943)

To determine the underlying cause of the collapse of a parachute, known as 'squidding.' Measurements of pressure were made in a wind tunnel at a number of positions over the surfaces of rigid models representing (a) a fully ...
Wind-tunnel flutter tests on a delta wing with an all-moving tip control surface

D. R. Gaukroger (1953)

Wind-tunnel tests on a half-span model delta wing, fitted with an all-moving tip control surface, are described. The model, which is flexible, has a leading-edge sweepback of 45 deg; and the control surface, which is rigid, ...
Wind-tunnel flutter tests on a model delta wing under fixed and free root conditions

D. R. Gaukroger; E. W. Chapple; A. Milln (1950)

Wind-tunnel tests on a model wing of delta plan form are described. Tests have heen made with the wing root fixed and also with the root free in pitch and vertical translation. Critical flutter speed and frequency are given ...

Now showing items 1262-1281 of 1313

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