Bristol Braemar: Difference between revisions
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The '''Bristol Braemar''' was a |
The '''Bristol Braemar''' was a British [[heavy bomber]] aircraft developed at the end of the [[World War I|First World War]] for the [[Royal Air Force]]. Only two [[prototype]]s were constructed. |
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==Development== |
==Development== |
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The prototype Braemar was developed in response to the establishment of the [[Independent Air Force]] in October 1917, as a [[bomber]] capable of the long-range bombing of [[Berlin]] if necessary. A large [[triplane]], it had internal stowage for up to six 250 lb (110 kg) bombs. |
The prototype Braemar was developed in response to the establishment of the [[Independent Air Force]] in October 1917, as a [[bomber]] capable of the long-range bombing of [[Berlin]] if necessary. A large [[triplane]], it had internal stowage for up to six 250 lb (110 kg) bombs. |
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The initial design featured |
The initial design featured an unusual engine installation with a central engine room housing all four engines. These were to be geared in pairs and power taken from the engines to the four propellers by power shafts. This design was abandoned early in development, and both the completed Braemars had a conventional engine installation, with the engines in inline tandem pairs, driving [[Push-pull configuration|pusher and tractor propellers]]. However, the engine-room design was resurrected later in the Braemar's development life, for the proposed steam-powered [[Bristol Tramp|Tramp]]. |
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A contract from the Air Board for three prototypes was awarded to Bristol & Colonial on 26 February 1918. The first prototype Braemar flew on 13 August 1918, with four {{convert|230|hp|kW|abbr=on}} [[Siddeley Puma]] engines. The prototype showed generally good performance with a top speed of {{convert|106|mph|km/h|abbr=on}}, but there were complaints from the test pilots about the view from the cockpit and the controls,<ref>The pilots were no longer able to feel sideslip through the wind on their faces ([http://www.flightglobal.com/pdfarchive/view/1960/1960%20-%200208.html ''Flight'' 12 February 1960 p208])</ref> and so the next aircraft produced was an improved version designated Braemar Mk.II. The Mk.II received considerably more power from its four {{convert|400|hp|kW|abbr=on}} [[Liberty L-12]] engines, which gave it an improved speed of {{convert|125|mph|km/h|abbr=on}}. |
A contract from the Air Board for three prototypes was awarded to Bristol & Colonial on 26 February 1918. The first prototype Braemar flew on 13 August 1918, with four {{convert|230|hp|kW|abbr=on}} [[Siddeley Puma]] engines. The prototype showed generally good performance with a top speed of {{convert|106|mph|km/h|abbr=on}}, but there were complaints from the test pilots about the view from the cockpit and the controls,<ref>The pilots were no longer able to feel sideslip through the wind on their faces ([http://www.flightglobal.com/pdfarchive/view/1960/1960%20-%200208.html ''Flight'' 12 February 1960 p208])</ref> and so the next aircraft produced was an improved version designated Braemar Mk.II. The Mk.II received considerably more power from its four {{convert|400|hp|kW|abbr=on}} [[Liberty L-12]] engines, which gave it an improved speed of {{convert|125|mph|km/h|abbr=on}}. |
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==Specifications (Braemar Mk.II)== |
==Specifications (Braemar Mk.II)== |
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{{Aircraft specifications |
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{{Aircraft specs |
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<!-- if you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] --> |
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|ref=Bristol Aircraft since 1910<ref name=Barnes>{{cite book |last=Barnes |first=C.H. |title=Bristol Aircraft since 1910 |year=1964 |edition=1st |publisher=Putnam & Company Ltd. |location=London |pages=138–142}}</ref> |
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|plane or copter?=plane |
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|prime units?=imp |
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|jet or prop?=prop |
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<!-- |
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|ref=Barnes C.H. (1964), p.142 |
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General characteristics |
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|crew=six - two pilots, wireless operator, engineer and two gunners |
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--> |
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|capacity= |
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|crew=6 - 2 pilots, wireless operator, engineer and two gunners |
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|length main=51 ft 6 in |
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|length |
|length ft=51 |
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|length in=6 |
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|span main=81 ft 8 in |
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|length note= |
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|span alt=24.89 m |
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|span ft=81 |
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|height main=20 ft |
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|span in=8 |
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|height alt=6.10 m |
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|span note= |
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|area main=1,905 ft<sup>2</sup> |
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|height ft=20 |
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|area alt=177 m<sup>2</sup> |
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|height in= |
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|empty weight main=10,650 lb |
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|height note= |
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|empty weight alt=4,840 kg |
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|wing area sqft=1905 |
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|loaded weight main=18,000 lb |
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|wing area note= |
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|loaded weight alt=8,170 kg |
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|aspect ratio=<!-- sailplanes --> |
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|airfoil= |
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|max takeoff weight alt=<!-- kg--> |
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|empty weight lb=10650 |
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|engine (prop)=[[Liberty L-12]] |
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|empty weight note= |
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|type of prop=[[inline engine (aviation)|inline engine]] |
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|gross weight lb=16500 |
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|number of props=4 |
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|gross weight note= |
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|power main=400 hp |
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|max takeoff weight lb= |
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|power alt=300 kW |
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|max |
|max takeoff weight note= |
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|fuel capacity= |
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|max speed alt=125 mph, 200 km/h |
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|more general= |
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|max speed more=at sea level |
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<!-- |
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|cruise speed main=<!-- mph--> |
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Powerplant |
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|cruise speed alt=<!-- knots, km/h--> |
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--> |
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|range main=more than 1,000 mi |
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|eng1 number=4 |
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|range alt=1,600 km |
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|eng1 name=[[Liberty L-12]] |
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|ceiling main=17,000 ft |
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|eng1 type=V-12 water-cooled piston engines |
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|ceiling alt=5,100 m |
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|eng1 hp=400 |
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|climb rate main= |
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|eng1 note=in two tandem nacelles mounted on the mid wing |
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|climb rate alt= |
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|loading main=9.45 lb/ft<sup>2</sup> |
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|prop blade number=2 |
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|loading alt=46.2 kg/m<sup>2</sup> |
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|prop name=fixed-pitch pusher and tractor propellers |
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|power/mass main=0.08 hp/lb |
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|prop dia ft=<!-- propeller aircraft --> |
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|power/mass alt=150 W/kg |
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|prop dia in=<!-- propeller aircraft --> |
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|prop dia note= |
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<!-- |
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Performance |
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--> |
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|perfhide= |
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|max speed mph=106 |
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|max speed note= |
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|max speed mach=<!-- supersonic aircraft --> |
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|cruise speed mph= |
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|cruise speed note= |
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|stall speed mph= |
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|stall speed note= |
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|never exceed speed mph= |
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|never exceed speed note= |
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|minimum control speed mph= |
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|minimum control speed note= |
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|range miles=1000 |
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|range note=+ |
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|combat range miles= |
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|combat range note= |
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|ferry range miles= |
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|ferry range note= |
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|endurance=<!-- if range unknown --> |
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|ceiling ft=17000 |
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|ceiling note= |
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|g limits=<!-- aerobatic --> |
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|roll rate=<!-- aerobatic --> |
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|glide ratio=<!-- sailplanes --> |
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|climb rate ftmin= |
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|climb rate note= |
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|time to altitude= |
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|wing loading lb/sqft=9.45 |
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|wing loading note= |
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|fuel consumption lb/mi= |
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|power/mass={{cvt|0.08|hp/lb}} |
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|thrust/weight= |
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|more performance=<!--</br> |
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*'''Take-off run:''' {{cvt||ft|0}} |
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*'''Take-off distance to {{cvt|50|ft|0}}:''' {{cvt||ft|0}} |
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*'''Landing run:''' {{cvt||ft|0}} |
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*'''Landing distance from {{cvt|50|ft|0}}:''' {{cvt||ft|0}}--> |
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<!-- |
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Armament |
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--> |
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|guns=2 × 0.303 in (7.7 mm) [[machine gun]]s |
|guns=2 × 0.303 in (7.7 mm) [[machine gun]]s |
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|bombs=1,500 lb (680 kg) |
|bombs=1,500 lb (680 kg) |
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==References== |
==References== |
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{{commons category}} |
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{{commonscat}} |
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===Citations=== |
===Citations=== |
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{{reflist}} |
{{reflist}} |
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===Bibliography=== |
===Bibliography=== |
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* {{cite book|author=Barnes C.H.|year=1964|title=Bristol Aircraft Since 1910|publisher=Putnam & Company Ltd|isbn=0-370-00015-3}} |
* {{cite book|author=Barnes C.H.|year=1964|title=Bristol Aircraft Since 1910|publisher=Putnam & Company Ltd|isbn=0-370-00015-3}} |
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Latest revision as of 14:10, 24 January 2023
| Bristol Types 24 and 25 Braemar | |
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| Braemar second prototype, 1919 | |
| Role | Heavy bomber |
| National origin | United Kingdom |
| Manufacturer | Bristol Aeroplane Company |
| Designer | Frank Barnwell |
| First flight | 13 August 1918 |
| Number built | 2 |
| Developed into | Bristol Pullman |
The Bristol Braemar was a British heavy bomber aircraft developed at the end of the First World War for the Royal Air Force. Only two prototypes were constructed.
Development[edit]
The prototype Braemar was developed in response to the establishment of the Independent Air Force in October 1917, as a bomber capable of the long-range bombing of Berlin if necessary. A large triplane, it had internal stowage for up to six 250 lb (110 kg) bombs.
The initial design featured an unusual engine installation with a central engine room housing all four engines. These were to be geared in pairs and power taken from the engines to the four propellers by power shafts. This design was abandoned early in development, and both the completed Braemars had a conventional engine installation, with the engines in inline tandem pairs, driving pusher and tractor propellers. However, the engine-room design was resurrected later in the Braemar's development life, for the proposed steam-powered Tramp.
A contract from the Air Board for three prototypes was awarded to Bristol & Colonial on 26 February 1918. The first prototype Braemar flew on 13 August 1918, with four 230 hp (170 kW) Siddeley Puma engines. The prototype showed generally good performance with a top speed of 106 mph (171 km/h), but there were complaints from the test pilots about the view from the cockpit and the controls,[1] and so the next aircraft produced was an improved version designated Braemar Mk.II. The Mk.II received considerably more power from its four 400 hp (300 kW) Liberty L-12 engines, which gave it an improved speed of 125 mph (201 km/h).
The Braemar never entered service with the RAF, and the two prototypes were the only Braemars built. The third prototype was completed as a Pullman 14-passenger civil transport.
Variants[edit]
- Type 24 Braemar I
- Prototype with four 230 hp (172 kW) Siddeley Puma engines, one built first flown 13 March 1918.
- Type 25 Braemer II
- Prototype with four 400 hp (298 kW) Liberty L-12 engines, one built first flown 18 February 1919.
- Type 26 Pullman
- 14-passenger civil transport variant with Liberty L-12 engines, one built first flown in May 1920.
Specifications (Braemar Mk.II)[edit]
Data from Bristol Aircraft since 1910[2]
General characteristics
- Crew: 6 - 2 pilots, wireless operator, engineer and two gunners
- Length: 51 ft 6 in (15.70 m)
- Wingspan: 81 ft 8 in (24.89 m)
- Height: 20 ft (6.1 m)
- Wing area: 1,905 sq ft (177.0 m2)
- Empty weight: 10,650 lb (4,831 kg)
- Gross weight: 16,500 lb (7,484 kg)
- Powerplant: 4 × Liberty L-12 V-12 water-cooled piston engines, 400 hp (300 kW) each in two tandem nacelles mounted on the mid wing
- Propellers: 2-bladed fixed-pitch pusher and tractor propellers
Performance
- Maximum speed: 106 mph (171 km/h, 92 kn)
- Range: 1,000 mi (1,600 km, 870 nmi) +
- Service ceiling: 17,000 ft (5,200 m)
- Wing loading: 9.45 lb/sq ft (46.1 kg/m2)
- Power/mass: 0.08 hp/lb (0.13 kW/kg)
Armament
- Guns: 2 × 0.303 in (7.7 mm) machine guns
- Bombs: 1,500 lb (680 kg)
See also[edit]
Related development
Aircraft of comparable role, configuration, and era
Related lists
References[edit]
Wikimedia Commons has media related to Bristol Braemar.
Citations[edit]
- ^ The pilots were no longer able to feel sideslip through the wind on their faces (Flight 12 February 1960 p208)
- ^ Barnes, C.H. (1964). Bristol Aircraft since 1910 (1st ed.). London: Putnam & Company Ltd. pp. 138–142.
Bibliography[edit]
- Barnes C.H. (1964). Bristol Aircraft Since 1910. Putnam & Company Ltd. ISBN 0-370-00015-3.
- "Two Tri-Quads", Flight: 209, 5 March 1942