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Browsing Aeronautical Research Council Reports & Memoranda by Issue Date

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Now showing items 1-20 of 1313

A solution of the laminar boundary-layer equation for retarded flow

D. R. Hartree (1939)

The laminar boundary-layer equation, for a linearly retarded velocity in the main stream, U = 1 - 1/8x in reduced variables, has been solved numerically by working in finite intervals in x, with a correction for the finite ...
Notes on the tail-first aeroplane

S. B. Gates (1939)

The tail-first aeroplane has certain strong attractions when combined with a tricycle undercarriage; in particular it has been suggested that it would represent a definite advance in the production of high lift. In these ...
The resistance of aluminium and beryllium bronzes to fatigue and corrosion-fatigue

D. G. Sopwith (1940)

The investigation of the fatigue and corrosion-fatigue resistance of special bronzes (Gough and Sopwith, 1937) is extended to include (1) aluminium bronze (D.T.D.I60), (2) beryllium bronze (2.25 per cent. Be), each in two ...
Tests on a whirlwind aircraft in the royal aircraft establishment 24-ft wind tunnel (in two parts)

T. V. Somerville; R. R. Duddy; G. H. L. Buxton (1940)

Tests were made in the 24-ft Wind Tunnel during March and April, 1940, on the Whirlwind aircraft to find if simple modifications can be introduced which will decrease its drag. The drag analysis is not complete and is ...
Note on differential gearing as a means of aileron balance

S. B. Gates (1940)

It has been suggested in some American investigations that differential gearing, combined with adjustment of the aileron floating angle by means of a tab, may be a powerful method of balancing ailerons. This report sets ...
Tests in the compressed air tunnel on the aerofoils NACA 0015 and NACA 0030 with and without split flap and on other aerofoils of various thicknesses with a split flap

R. Jones (1940)

To obtain information on the effect of thickness on the aerodynamic characteristics of aerofoils with and without a split flap. The following 4 ft. by 8 in. rectangular aerofoils were tested :- NACA 0015 and NACA 0030 with ...
Notes on the lift and profile drag effects of split and slotted flaps

A. D. Young; P. A. Hufton (1941)

The existing data have been analysed and a method has been derived for predicting the lift and profile-drag increments of split and slotted flaps. It is suggested that the probable order of error involved in the method is ...
Flight tests on a falcon with spoiler lateral control

C. E. Kerr (1941)

As part of a general investigation of tile use of spoilers for lateral control, flight tests were required on a Falcon with retractable circular-arc spoilers. In the first stage of the flight tests pilots' impressions and ...
Spar depth and weight

W. Tye; R. G. Thorne (1941)

In all classes of structural design it is the usual practice to employ deep rather than shallow beams. This arises from the fact that, within limits defined partly by the web construction, the deeper the beam the less the ...
Flight tests of a youngman flap on fairey P.4/34. K.7555

M. B. Morgan; D. E. Morris (1941)

Full-scale tests were required of the lift and drag characteristics of the Youngman flaps fitted to Fairey P.4/34 K.7555. These flaps are of the external aerofoil type, and can be lowered to two positions, one giving medium ...
Stress concentration due to four-point fixing at front end of monocoque fuselage, theoretical analysis

M. Fine; D. Williams (1941)

This report is a sequel to previous work by Williams, Starkey and Taylor (R. & M. 2098) and by Williams and Fine (R. & M. 2099) and treats the problem of the stress distribution in a stringer-reinforced cylindrical shell ...
Propeller blade vibration nature and severity of vibration at edgewise resonance as influenced by coupling effects due to blade twist

J. F. Shannon; J. R. Forshaw (1941)

Information was required as to the stress distribution in propeller blades occurring at edgewise resonance, and the importance of this vibration relative to the other modes. Tests were carried out on a duralumin-bladed ...
Lateral control with high lift devices

A. D. Young; R. R. Duddy (1941)

The increasing attention which high-lift devices are receiving makes it desirable that a summary of the present information on lateral control with high-lift devices should be available. The devices considered are classified ...
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 ...
Comparison between plain and stringer-reinforced sheet from the shear lag standpoint

M. Fine (1941)

In R. & Ms. 2098, 2099, 2100 the stringer-sheet method of solving shear lag problems in stringer reinforced sheet was developed. The present report compares for two simple cases the solution for the plain sheet with that ...
Tests on the hurricane L.1696 in the 24-ft wind tunnel

D. W. Bottle; T. V. Sommerville (1941)

Tests on a Hurricane in the 24-ft Wind Tunnel at the Royal Aircraft Establishment were required to find if any simple modifications could be made which would reduce its drag. Measurements were made of :- (1) Leak drag. (2) ...
Interference velocity for a close pair of contra-rotating airscrews

C. N. H. Lock (1941)

A method is developed of calculating the performance of a pair of contra-rotating airscrews, closely analogous to that described in R. & M. 2035 a for a single airscrew. The assumptions made are considered to be theoretically ...
Note on Wind-Tunnel Measurements of Yawing Moment, Rudder Fixed and Free, on Models of Three Aircraft

Adamson, J E; Brown, E C; Allen, R H (His Majesty's Stationery Office, 1941-07)
Wind-tunnel tests on the spoiling effects of engine cooling gills on radial air-cooled installations on a wing

J. Seddon; J. A. Kirk (1942)

Information was required on the spoiling drag associated with opening cooling gills on radial air-cooled engine installations on a wing. Maximum lift, drag up to high CL, and cooling flow were measured on a 1/12 scale model ...
Some wind-tunnel developments of the spoiler as a form of lateral control

W. S. Coleman; G. H. Tidbury (1942)

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 ...

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