Bristol Low Volume Production

Two seat biplane glider designed by George Challenger for company founder Sir George White to present to the Bristol and West of England Aero Club after he had been elected president of the club in October 1910. It featured a foreplane well ahead of the wings, mounted on wire-braced wooden booms, which also carried the undercarriage of a pair of long skids carrying small wheels. Four booms, tapering together in elevation, carried a single tailplane rather than the pair used by the Boxkite.[2] The foreplane and tailplane moved together to control pitch. A small pair of rudders was mounted between the booms near the tail. Lateral control was by ailerons fitted on the upper wing. It had been designed to have a 30 h.p. engine fitted but this was never installed.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW
32 ft 4 in	33 ft 10 in	6 ft 8 in
9.86 m	10.31 m	2.03 m

Single-seat biplane designed to combine the performance of a monoplane but using the strength of the biplane. Designed by Robert Grandseigne and Léon Versepuy, supervised by George Challenger, it had unequal span wings each with a single steel-tube spar. The rectangular fuselage was a composite structure of wood and steel tubes covered in fabric. It had a twin-skid steel-tube chassis fitted with two wheels on a rubber-sprung cross axle and also had a tail skid, the main skids were long enough to act as brakes on landing. One 50 h.p. Gnome powerplant.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
27 ft	25 ft		210 sq ft	570 lb	750 lb		55 mph/ 48 kn
8.23 m	7.62 m		19.51 m2	259 kg	340 kg		89 km/h

Single seat monoplane designed by George Challenger and Archibald Low. It used features from both the Bleriot (warping wings) and Antionette (triangular-section fuselage) designs. Two triangular rudders were fitted at the sternpost, above and below the tailplane and elevators. One 50 h.p. Gnome powerplant.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
33 ft 6 in	31 ft 6 in		215 sq ft	580 lb	760 lb		55 mph/ 48 kn
10.21 m	9.6 m		19.97 m2	263 kg	345 kg		89 km/h

Two seat biplane seaplane, design of which was not finalised at time of cancellation. 200 h.p. Canton-Unné powerplant (but see note 1).

Two seat all metal reconnaissance biplane. Designed by Frank Barnwell, it borrowed from marine experience by using duralumin sheet, varnished to prevent corrosion and used these to make the fuselage in four sections. The two forward sections were semi-monocoque (i.e. open channels) with braced longitudinal upper members which, bolted together, held the engine and the pilot's cockpit. Aft, two more sections, both true monocoques, held the observer and carried the tail unit. The two cockpits were close together, with the pilot under the wing at mid-chord and the observer under a trailing edge cutout. Barnwell proposed that the short observer's fuselage section should be removable to turn the M.R.1 into a single-seater, though this configuration was not realised. The monocoque sections were very early examples of double-skinned construction, with a smooth outer skin riveted to a longitudinally-corrugated inner skin. The complete fuselage was of round-cornered rectangular cross-section and quite slender, mounted between the wings. The M.R.1 was a two-bay biplane without stagger or sweep, with ailerons on both planes. Aluminium wing spars proved difficult to make sufficiently rigid and Bristol outsourced their manufacture to The Steel Wing Company at Gloucester, who had built experimental steel wings for other aircraft. Armament comprised one forward firing 0.303 in Vickers machine gun and one Scarff-mounted 0.303 in Lewis gun
With the fuselage of the first M.R.1 completed before the wings, Bristol decided to make a set of conventional wooden wings, with ailerons only on the upper planes, for flight trials in mid-1917, fitted with a 140 h.p. Hispano Suiza powerplant
The second M.R.1 did not fly until late in 1918 when the metal wings were at last ready, powered by a 180 hp (130 kW) Wolseley Viper powerplant.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Endurance	Service Ceiling
42 ft 2 in	27 ft 3 in	10 ft	458 sq ft	1700 lb	2810 lb	91 mph/ 79 kn	110 mph/ 96 kn	5 hrs
12.85 m	8.31 m	3.05 m	42.55 m2	771 kg	1275 kg	146 km/h	177 km/h

General-purpose six-passenger/cargo biplane designed by Frank Barnwell in February 1919. 75 ft wingspan with a wing area of 1,150 sq.ft. One 500 h.p. Siddeley Tiger powerplant.

General-purpose three-passenger/cargo biplane designed by Frank Barnwell in October 1919. One150 h.p. RAF 4a or Siddeley Lynx powerplant.

General-purpose eight-passenger/cargo biplane designed by Frank Barnwell in late 1919. Four 100 h.p. Cosmos Lucifer powerplants.

Proposed variant of the Grampus IV for the American market with two Hall-Scott powerplants.

Single seat racing monoplane, built primarily to demonstrate the capabilities of the Bristol Jupiter engine. Designed by Wilfrid Thomas Reid (b. 4 March 1887 in Battersea – d. 5 April 1968 in Newton Abbot, Devon), it was a single-engined mid-wing monoplane with a retractable undercarriage. The engine was entirely enclosed within the circular-section fuselage, with an elaborate arrangement of ducts to channel cooling air over the cylinders. A large spinner with a central opening to admit air, constructed of laminated wood with internal wire bracing was fitted. The fuselage, which increased in diameter until the trailing edge of the wing and then tapered to a point, was built around a pair of circular steel frames to which the wing root stubs were mounted: aft of this structure it was a semi-monocoque built up from three laminations of tulipwood over hoops which were braced with radial wires. The fabric-covered wings had composite steel-and-wood spars and were designed as cantilevers, without bracing wires, and were parallel-chord with raked tips and deep full-span ailerons, which accounted for about 20% of the wing's chord. The undercarriage was operated by a handcrank and chain drive, the legs being housed in channels in the fuselage and the wheels within the wing roots. One 480 h.p. Bristol Jupiter powerplant.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
25 ft 2 in	21 ft 7 in	8 ft 8 in					220 mph/ 191 kn
7.67 m	6.58 m	2.64 m					354 km/h

Two seat day or night bomber to Specification 26/23, designed by Wilfrid Reid and Clifford Tinson. It was a fabric-covered all-metal structured three-bay biplane, with equal span, unswept and unstaggered wings with Frise-type ailerons on the upper and lower planes. Structurally, the wings were of rolled steel and duralumin. The fuselage was built from steel tubes and had a rectangular cross section. The pilot sat forward of the leading edge of the wing in an open cockpit and the gunner/observer in a cockpit well aft, fitted with a ring-mounted .303 in Lewis Gun. He could also access a bomb aimer's position, when he lay prone on the aircraft floor. The horizontal tail was positioned at the top of the fuselage and braced below, carrying elevators whose balances protruded beyond the fixed surfaces. The rudder was tall and also horn-balanced, but more elegantly than the elevators with the edge running smoothly into the fin. The undercarriage was of wide track, mounted to the wings below the centre section interplane struts and braced to the fuselage. The wings of the first two Berkeleys were of wooden construction for speed of completion, with the third all metal. Offensive armament included a single 550 lb bomb under fuselage, or two 230 lb bombs underwing. Leitner-Watts Metal airscrews were required for the second and third machine. One 650 h.p. Rolls Royce Condor III powerplant.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
57 ft 11 in	47 ft 6 in	14 ft	985 sq ft	5200 lb	8128 lb	100 mph/ 87 kn	120 mph/ 104 kn	860 mi	17900 ft
17.65 m	14.48 m	4.27 m	91.51 m2	2359 kg	3687 kg	161 km/h	193 km/h	1384 km	5456 m

Two seat biplane built to determine the differences between wind tunnel models and full scale for radial engine cowlings. It was a two-bay biplane without stagger or sweep on the equal span, square-tipped wings. These and the tail unit, which was also very rectangular and simple, were fabric-covered steel strip and tube structures. Part of the Type 92's odd appearance came from the wish to minimise wing-fuselage aerodynamic interactions. To achieve this, the vertical gap between the wings was large: at 9 ft it was 25% of the span. The undercarriage had a wide track and was a single axle arrangement mounted below the ends of the inner interplane struts. The fuselage was also simple, the structural part being a plywood-covered box girder about 2 ft square from the nose to aft of the second cockpit, where it tapered in plan only to an edge at the tail. Two streamlined pylons joined the wings to the box, above and below, carrying the fuselage at mid gap. For the aerodynamic investigations, the untapered part of the fuselage could be contained in circular fairings of different diameters; originally a range of five sizes was planned, but to reduce cost only the smallest (3 ft) and largest (5 ft) were flown. Since the diameter of the Jupiter was about 4 ft 7 in, the cylinder heads were well exposed with the smaller fairing and enclosed by the larger. One 450 h.p. Bristol Jupiter VI powerplant.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
36 ft	29 ft 4 in	13 ft	432 sq ft	2200 lb	3400 lb		132 mph/ 115 kn	4924 mi	26000 ft
10.97 m	8.94 m	3.96 m	40.13 m2	998 kg	1542 kg		212 km/h	7924 km	7925 m

Three seat heavily armed monoplane fighter to Specification F.4/24. It was a high-wing all-metal monoplane with an unusual triangular-section fabric-covered steel-tube fuselage with two upper longerons and a single lower member. The pilot sat in line with the wing's leading edge, with one gun position in the nose and another just behind the wing. The two-spar wing had a steel primary structure and duralumin nose ribs and end-members, and was a semi-cantilever, being braced by a pair of diagonal struts on each side. The legs of the fixed undercarriage met the wing at the same place as the struts and had an axle fairing of airfoil section, contributing some lift. Provisions were made for two 37 mm Coventry Ordnance Works cannon, one in nose and one midships, plus .303 in Lewis guns in the same positions, but the armament not installed. Two 450 h.p. Bristol Jupiter VI powerplants.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
70 ft	44 ft 11 in	9 ft 6 in	840 sq ft	5100 lb	8195 lb	108 mph/ 94 kn	125 mph/ 109 kn
21.34 m	13.69 m	2.9 m	78.04 m2	2313 kg	3717 kg	174 km/h	201 km/h

Two seat single-bay biplane fighter of mixed construction. The fuselage was a box-girder spruce structure, reinforced with plywood and steel-plate fittings, with aluminium cladding from the pilots cockpit forward, plywood cladding aft. The two-spar staggered wings were fabric covered, with spars built up of rolled-steel strips riveted together. The lower centre section was supported on struts below the fuselage and Frise ailerons were fitted on the lower wing only. The pilot's cockpit was located near the top-plane trailing edge, and immediately behind which was the gunner's cockpit, fitted with a .303 in Lewis machine gun on a Scarff ring, mounted on a plywood structure. Forward armament consisted of two synchronised .303 in Vickers machine guns The tail plane was a wooden cantilever structure mounted on the top of the fuselage, having two spruce and plywood box spars. The tailplane incidence was adjustable in flight. A V-type undercarriage was employed in which the front struts were fitted with oleo shock absorbers. Fuel was fed entirely by gravity; two tanks of 29 gals. capacity each, mounted in the upper wings, while a third tank, of 20 gals. capacity, located in the upper portion of the fuselage immediately behind the fireproof bulkhead. One 450 h.p. Bristol Jupiter VI powerplant.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
33 ft 7 in	27 ft 4 in	9 ft 6 in	360 sq ft	2100 lb	3540 lb	140 mph/ 122 kn	160 mph/ 139 kn		21000 ft
10.24 m	8.33 m	2.9 m	33.45 m2	953 kg	1606 kg	225 km/h	257 km/h		6401 m

Single seat fighter to Specification F.20/27. It was an unequal span single bay biplane with a single pair of N interplane struts, the structure being all-metal with a fabric covering. The wing featured teel tube spars and trailing edge, a duralumin sheet leading edge, and steel strip for the remainder. The top centre plane was wire braced inside, the bottom centre plane strut braced to withstand undercarriage stresses. The forward fuselage was of high-tensile steel tube construction with a solid forged steel ring engine mounting carried on and braced by high tensile steel tubes. The rear fuselage was of high-tensile strip steel construction. The fin and tailplane were of high-tensile steel tube framework with channel section duralumin ribs and aluminium leading edge. In order to optimise the pilot's field of view there was large semi-circular cutout in the trailing edge of the upper wing and the inboard section of the lower wing was of reduced chord. Frise ailerons were fitted to the top wing only. It was armed with a pair of 0.303 in Lewis guns mounted on either side of the cockpit. One 480 h.p. Bristol Mercury IIA powerplant driving a two-bladed propeller.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
30 ft	23 ft 6 in	9 ft 5 in	230 sq ft	1910 lb	2850 lb	160 mph/ 139 kn	190 mph/ 165 kn
9.14 m	7.16 m	2.87 m	21.37 m2	866 kg	1293 kg	257 km/h	306 km/h

Two-seat biplane built for an attempt on the world distance record. It was a large single engine, two-bay biplane, featuring an enclosed cockpit for the two crew in tandem. The wings featured parallel interplane struts with wire bracing; ailerons were fitted to all mainplanes. The tailplane was strut braced to the rear fuselage and the large rudder horn balanced. Integral aluminium fuel tanks were located in both upper and lower mainplanes inboard of the inner interplane struts, with noticeable external stiffening, though the fuel system was later redesigned to accommodate steel tanks of reduced capacity. At the same time the ailerons were modified with an inset horn balance. One 480 h.p. Bristol Jupiter VIII piston powerplant driving a four bladed propeller.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
51 ft 2 in	37 ft 9 in	14 ft	700 sq ft	4600 lb	9800 lb	90 mph/ 78 kn		3300 mi
15.6 m	11.51 m	4.27 m	65.03 m2	2087 kg	4445 kg	145 km/h		5311 km

Four-passenger biplane aimed at the charter market, to Specification 19/28. A slightly enlarged version of a projected Type 110 three-passenger aeroplane, it was a single-engine, single-bay all-metal, fabric-covered biplane. The wings were unswept, unstaggered and of almost equal span, but the lower plane was of much narrower chord than the upper. The wing box spars were of corrugated steel strip, and ribs of the same material. The internal drag struts were steel tubes with tie-rod drag bracing. The leading edges were of sheet aluminium, and the trailing edges of steel tubing. Frise ailerons were fitted to the top planes only. The inter-plane struts were built up of nickel-chrome steel strip, with steel fairings. The flat-sided fuselage was composed of several sections bolted together.The engine mounting plate was supported by four tubular struts braced by tie rods, and formed a complete unit bolted at the corners to the fuselage longerons. The pilot's cockpit was of tubular construction, and having tie rod bracing in the bottom panels and a Warren girder in the side panels. The passenger cabin structure was built up of high-tensile steel strip, the struts being of a corrugated section. The rear portion of the fuselage was of steel strip construction, while the extreme stern portion was composed of the stern post, four longerons and a pair of diagonal side panel struts, all of nickel chrome steel. It had a horn-balanced rudder and an unbraced horizontal tail carrying unbalanced elevators. A split undercarriage was fitted, with wide track main wheels and a tailskid. Long oval section rubber compression blocks being used in conjunction with oleo damping gear, the undercarriage members all being faired with Balsa wood and aluminium.
The passenger cabin, located between the wings, had three windows on each side, one of which was on the starboard side door. The cabin was 6 ft. long by 3 ft. 6 in. wide, the two front seats having back rests to fold down. In addition, one seat was hinged to fold against the wall of the saloon so as to allow of easy access to the pilot's cockpit. The bench type rear seat extended right across the cabin. The pilot sat high ahead of the leading edge of the upper wing in a glazed cockpit behind the completely cowled engine. The pilot's seat was placed on the port side, and was provided with a door on the starboard side. One 220 h.p. Titan or 315 h.p. Neptune powerplant.

Specification (Neptune powerplant)
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
40 ft 6 in	33 ft 6 in	10 ft 2 in	389 sq ft	2330 lb	4360 lb	100 mph/ 87 kn	125 mph/ 109 kn	620 mi
12.34 m	10.21 m	3.1 m	36.14 m2	1057 kg	1978 kg	161 km/h	201 km/h	998 km

Single seat half scale flying model of the Type 172 to Specification E.8/47 to meet the requirements of OR.250. One 5,500 lb thrust Rolls Royce Nene powerplant. Of all wood construction, it featured a 45 degree swept wing and 65 degree swept tailplane. Design work was completed, but the project cancelled.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW
45 ft 10 in	42 ft 3 in		435 sq ft		26000 lb
13.97 m	12.88 m		40.41 m2		11793 kg

Prototype of an unmanned short range expendable bomber to Specification UB.109T to meet the requirements of OR.1097. Production versions of the T-tailed Type 182 - with its swept wings set on top of the fuselage – were to have been made from Durestos, a non-strategic asbestos phenolic material, but the prototype Type 182R – R standing for retrievable - was made of metal and was fitted with a retractable undercarriage. One Armstrong Siddeley Viper powerplant.

A number of variations for a Supersonic Transport Aircraft design were investigated under the generic Type 198. The final configuration seated 136 passengers in economy seating, or up to a maximum of 146, along with a crew of four. It featured an ogival wing with a structure primarily of aluminium and six 22,000 ib.s.t. Bristol Olympus 593 powerplants. A smaller derivative, the BAC 223, eventually led to the BAC Concorde.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed*	Maximum Speed	Range	Service Ceiling
84 ft	188 ft 5 in		5000 sq ft		385000 lb	Mach 2.2
25.6 m	57.43 m		464.52 m2		174633 kg