Beardmore Low Volume Production

Two seat biplane seaplane intended for the 1914 Round Britain race. It was built of steel tubing, with a rectangular fuselage built around four longerons. To these were attached tubular steel struts and cross members, all secured by welding. the crew of two were carried in an aluminium upper fuselage shaped like a 'turtle back', with two cut outs for the cockpits, while the lower fuselage was fabric covered. The wing was highly swept and staggered, with inversely tapered ailerons on the upper wing only. Fin and tailplane were both triangular and of very low aspect ration, fitted with unbalanced rudder and elevators. One 120 h.p. Beardmore-Austro-Daimler powerplant.

D.F.W. Tractor Biplane Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
44 ft	25 ft		450 sq ft	1500 lb			85 mph/ 74 kn
13.41 m	7.62 m		41.81 m2	680 kg			137 km/h

Six passenger folding wing biplane transport. The passengers entered the cabin via a door on the port side aft of the wings, while the pilot was located in an open cockpit aft of the passenger door. The wings were of unequal chord and featured slight dihedral, with ailerons on the upper wing only. One 500 h.p. Beardmore Galloway Atlantic powerplant.

W.B.VIA Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
62 ft	42 ft 6 in	13 ft 6 in	934 sq ft		7540 lb		120 mph/ 104 kn
18.9 m	12.95 m	4.11 m	86.77 m2		3420 kg		193 km/h

Shipboard fighter. Nothing else known.

Ten seat three bay amphibian biplane. The wings were of unequal chord and featured a small amount of dihedral outboard of the centre section. The outer wing panels could be folded to reduce hangar space. The tail surfaces were carried on twin wire braced tail booms, parallel in plan but tapered in side elevation, and featured twin fins and rudders, with triple tailplanes and elevators. The four engines were located in an 'engine room' inside the hull, arranged in pairs, two either side, separated by a gear-box. The two tractor propellers were mounted on gear boxes attached to the middle of the inner wing struts, and shaft driven from the engines. The hull was formed of 16 longitudinal duralumin girders spaced around circular frames, built up of top and bottom channels forming the flanges of the girders, braced by light airship type lattice bars. The transverse formers were spaced 2 ft. apart, and fitted in as segments between the longitudinal girders. The keelson and chines were of rock elm whilet the structure supporting the chines was a series of duralumin cantilever girders of similar general design to that of the main longitudinal and transverse girders. The outer covering of the hull consisted of two skins of mahogany, the inner skin being laid diagonally, the outer one longitudinally, with a layer of fabric placed between the two skins, varnished and nailed in place, adding to the water-tightness of the hull. The lower part of the hull was divided into six watertight compartments. The passenger cabin was divided into two-compartments by the engine room, the front cabin, in the nose of the hull, seating two and the aft cabin seating four with a table, or six without. If necessary an extra passenger could be accommodated in the pilot's cabin. The pilot was placed in a separate cabin above the engine room, with Triplex glass windows in the side. These windows can be raised and lowered so as to provide not only ventilation but also a free view during rainy or foggy weather. A door in the side of the pilot's cabin led to a walking-way on the lower plane, while the engine room below was reached via a trap-door in the floor. Four 200 h.p. Beardmore Adriatic powerplants

W.B.IX Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
107 ft	61 ft	20 ft 6 in	2202 sq ft	9520 lb	14000 lb		93 mph/ 81 kn	403 mi
32.61 m	18.59 m	6.25 m	204.57 m2	4318 kg	6350 kg		150 km/h	649 km

Two seat all metal, two bay biplane passenger transport. The circular section fuselage was similar to the W.B.IIB, but redesigned in metal, as has the tailplane. Construction was chiefly of duralumin, made up into lattice girders. The fuselage featured four longerons, built up of two channel section flanges, with 'X' bracing in the form of a series of lattice bars, joined by transverse formers and crossbraced by diagonal channel section tie rods, placed back-to-back and riveted at the point where they cross one another. To this main structure were added stringers to bring the outside form up to a streamline shape. The duralumin spars of the short wing roots were built into the fuselage and externally braced to fuselage formers. A fireproof fuel tank was located immediately behind the engine, and behind that the passenger's cockpit, featuring a hinged glazed roof. To facilitate access to this cockpit, the trailing portion of the top plane centre section was hinged along the rear spar so that when folded up it lay flat on top of the top plane. The pilot was located in an open cockpit aft of the wing trailing edge. The heavily staggered, unequal chord, wings featured ailerons on the upper wing only. One 185 h.p. Beardmore powerplant.

W.B.X Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
46 ft	26 ft	11 ft	540 sq ft	1852 lb	2849 lb		91 mph/ 79 kn	400 mi
14.02 m	7.92 m	3.35 m	50.17 m2	840 kg	1292 kg		146 km/h	644 km

Two seat single bay biplane fighter. The slab-sided fuselage was of hexagonal section and fairly small cross-sectional area and of almost constant depth along its length. The fuselage was located between the mainplanes, the top plane roots being anchored to cabane struts from the top longerons, and the lower plane centre-section bolted to a fin built integral with the bulkheads of the fuselage. The fuselage comprised spruce longerons with bulkheads of spruce and three-ply, covered in birch three-ply, then with fabric, painted and doped to give a watertight surface. The fin carrying the lower plane, etc., was built integral with the fuselage bulkheads. A fireproof bulkhead was fitted at the front of the fuselage, and all parts forward of this being of steel. The engine bearer was of simple and rigid type, designed to allow the rapid removal of the complete engine unit, which was totally cowled-in with the exception of the exhaust collectors, with the Lamblin radiator located on the leading edge of the bottom centre section. To ensure close interaction between the pilot and the gunner, their cockpits were are located very close to each other. The pilot was located directly below a semicircular notch in the trailing edge of the upper wing.
The wings were rigidly braced by three struts on each side, one being the interplane I-strut with forked ends, and the other two compression struts running from the top longerons to the lower wing spars. The attachment to the fuselage is by pin joints, so that the wings can be quickly dismantled and re-erected. The two lift struts running from the fuselage down to the bottom plane were of steel tubing with duralumin fairings riveted on. The interplane I-strut was of built-up duralumin plate, faired to a streamline form. The upper and lower wings were of equal, constant, chord, but unequal span, with the lower wing having pronounced sweepback of 5.8°. Of identical construction, each comprised two box spars of spruce with ribs made of spruce and three-ply, the whole being covered with plywood from the leading edge to the rear spar. Ailerons were fitted on both wings. The wings were covered with linen fabric laid on at an angle of 45° to the leading edge. The tail unit was designed with a minimum of bracing, so as to improve the gunner's field of fire and, instead of the usual trimming tail, was fitted with a hinged leading edge operated from the cockpit. The undercarriage was of all-metal construction, the landing shocks are taken on a novel system of chrome-vanadium steel spiral springs under compression. The telescopic front legs of the undercarriage ran to the lower longerons of the fuselage, while the bent axles and rear chassis struts were connected to the vertical fin at the points of attachment of the lower wing spars. The tail skid was of all-metal construction, and landing shocks were taken by steel springs. One 360 h.p. Rolls-Royce Eagle IX powerplant.

W.B.XXVI Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
37 ft	27 ft 11 in		356 sq ft	2555 lb	3980 lb	121 mph/ 105 kn	145 mph/ 126 kn	4 hr	20000 ft
11.28 m	8.51 m		33.07 m2	1159 kg	1805 kg	195 km/h	233 km/h		6096 m