Browsing by Author "A. B. Haines"

24-ft wind tunnel tests on a propeller with NACA 16 series sections. Test results and analysis into mean lift-drag data

A. R. C. MacDougall; A. B. Haines (1948)

This report gives the results of tests made in the Royal Aircraft Establishment 24-ft Wind Tunnel on the de Havilland propeller for the Aeronautical Research Council research programme initiated in 1943. The propeller was ...

24-ft. tunnel tests on a Rotol wooden Spitfire propeller. Test results, and data for single radius calculations

A. B. Haines; P. B. Chater (1946)

This note contains the results of tests made in the Royal Aircraft Establishment 24-ft. tunnel on the Rotol hydulignum propeller RA.10046 designed for the Spitfire IX aircraft. The overall thrust and torque measurements ...

Aerodynamic loads on external stores a review of experimental data and method of prediction

P. Marsden; A. B. Haines (1962)

Summary. A survey has been made of the available literature on the aerodynamic loads associated with the external carriage of pylon-mounted stores adjacent to wing-fuselage combinations. The existing methods for estimating ...

Afterbody drag measurement at transonic speeds on a series of twin and single jet afterbodies terminating at the jet-exit

O. M. Pozniak; A. B. Haines (1973)

The calculation of the velocity distribution due to thickness for swept wings with subsonic edges at supersonic speeds

A. B. Haines; K. Rollins; J. Osborn (1962)

The centre-line mach-number distributions and auxiliary-suction requirements for the A.R.A. 9-ft X 8-ft transonic wind tunnel

A. B. Haines; J. C. M. Jones (1958)

Under review

A comparison of results in the A.R.A. transonic tunnel on a small and a large model of a slender wing

T. E. B. Bateman; A. B. Haines (1961)

Force, moment and pressure-plotting measurements are reported on 75 deg slender wings of 60 in. and 20 in. lengths in the Aircraft Research Association 9 ftx 8 ft perforated-wall transonic tunnel. The object of the tests ...

A comparison of wing pressure distributions measured in flight and on a windtunnel model of the super VC. 10

G. C. Browne; T. E. B. Bateman; M. Pavitt; A. B. Haines (1972)

It is generally assumed--or at least, hoped--that pressure distributions measured on windtunnel models apply directly to the full-scale aircraft and that they can therefore be used for aerodynamic appraisal and for stressing ...

The effect of differing thickness distributions on a propellor's efficiency

A. B. Haines (H. M. Stationery Office, 1944)

Calculations of the efficiency of propellors having five different thickness distributions (effects of other variants having been eliminated) have been made for forward speeds from 300 to 600 m.p.h. at 20,000 ft. It is ...

The effect of leading-edge geometry on high-speed stalling

G. F. Moss; A. B. Haines; R. Jordan (1973)

High-speed wind-tunnel tests on six wings of 40-deg sweepback, with various section shapes

L. N. Holmes; A. B. Haines (1952)

Tests have been made in the Royal Aircraft Establishment High-Speed Wind Tunnel on six wings, all of the same plan form (aspect ratio 3.5, taper ratio 0.4, quarter-chord sweep 40 deg) and thickness/chord ratio (10 per cent) ...

Pressure plotting tests in the Royal Aircraft Establishment high speed wind tunnel on a 21 per cent thick, low drag aerofoil (Brabazon 1 wing root section)

A. B. Haines; W. Port (1947)

Pressure plotting tests have been made on the 21 per cent thick wing root section for the Brabazon I aircraft as a two-dimensional aerofoil spanning the Royal Aircraft Establishment High Speed Tunnel The tests covered a ...

Some notes on the flow patterns observed over various swept-back wings at low Mach numbers (in the R.A.E. 10-ft x 7-ft high speed tunnel)

A. B. Haines (1954)

This paper collects together the flow patterns observed by an oil film (titanium oxide) technique over ten different Swept-back wings at high incidence and low Mach number in the Royal Aircraft Establishment 10-ft X 7-ft ...

Tests in the R.A.E. 10-ft x 7-ft high speed wind tunnel on drop tanks fitted to two swept-back wings Part 1 Comparison of under-wing and wing-tip installations Part 2 Comparison of various under-wing drop-tank arrangements

D. E. Hartley; A. B. Haines (1952)

The report describes tests made in the Royal Aircraft Establishment 10-ft × 7-ft High Speed Wind Tunnel on drop tanks, fitted to two wings, having the same plan-form with a sweepback of 40 deg and an aspect ratio of 3.5, ...

Tests in the Royal Aircraft Establishment 10-ft x 7-ft high-speed tunnel on 50-deg swept-back wings. Part I. Three of 7.5 per cent thickness. Part II. One of 7.5 per cent thickness with stall fences and leading-edge chord extension

A. B. Haines; C. W. Rhodes (1954)

Tests have been made in the Royal Aircraft Establishment 10-ft x 7-ft High-Speed Tunnel on three half-wings having a sweepback of about 50 deg on the quarter-chord line and 7.5 per cent thick sections. Two of the wings had ...

Browsing by Author "A. B. Haines"

Browsing by Author "A. B. Haines"

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