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Browsing Aeronautical Research Council Reports & Memoranda by Author

Browsing Aeronautical Research Council Reports & Memoranda by Author "A. B. Haines"

Now showing items 1-11 of 11

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 ...
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 ...
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 Aeronautical Research Council Reports & Memoranda by Author "A. B. Haines"

Browsing Aeronautical Research Council Reports & Memoranda by Author "A. B. Haines"

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