Armstrong Whitworth Low Volume Production

Three-seat carrier-borne fleet reconnaissance aircraft to Specification 8/20. Adapted from the Airco DH.9A, with added provision for an observer and wing stagger removed. One 400 h.p. Liberty powerplant. Further development was passed on to Westland, who further modified the aircraft to produce the Walrus.

Four-bay staggered biplane troop transport with two crew and capacity for 25 troops, to Specification D of R Type 12 (later 5/20). It featured a tubular-steel-framed box-like fuselage, wooden wings incorporating substantial hinges to allow them to be folded for storage, and a three-rudder, biplane tail. The pilot and navigator sat in open cockpits atop the nose. Two 450 h.p. Napier Lion powerplants.

Awana Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
105 ft 6 in	68 ft	20 ft 3 in	2300 sq ft	10000 lb	24100 lb		97 mph/ 84 kn	360 mi	8000 ft
32.16 m	20.73 m	6.17 m	213.68 m2	4536 kg	10932 kg		156 km/h	579 km	2438 m

Two seat "aerodynamic experimental" biplane to Specification 48/22. Like the Wolf, the tubular-steel-framed box-like fuselage was mounted on struts between the two sets of wings. The fuselage could be changed in length, different fins and tailplanes could be fitted, the incidence angle of both the tailplane and the unswept, equal chord wings could be altered, and the wings could be additionally changed in stagger (from zero to 30 deg.), gap (from 4 ft to 9 ft 6 in) and dihedral (from zero to 7 deg.). Additionally, the entire tail was a single unit and the incidence angle of the tailplane could not be changed without also changing that of the fin. One 180 h.p. Armstrong Siddeley Lynx III powerplant.

Ape Specification
Span	Length (Min/Max)	Height (Min/Max)	Wing Area	Empty Wt (Min/Max)	Max AUW (Min/Max)	Cruise Speed	Maximum Speed	Range	Service Ceiling
40 ft	28 ft 3 in	13 ft	473 sq ft	2020 lb	2700 lb		90 mph/ 78 kn		6400 ft
12.19 m	8.61 m	3.96 m	43.94 m2	916 kg	1225 kg		145 km/h		1951 m
	38 ft 3 in	15 ft		2570 lb	3250 lb
	11.66 m	4.57 m		1166 kg	1474 kg

Two/three seat single-bay biplane general purpose, bombing and torpedo-carrying aircraft to Specifications G.4/31, to meet the requirements of OR.2, and 38/34 (OR.10). It featured unswept, constant chord wings of mild stagger, fabric covered over a structure built up around rolled-steel strip spars and aluminium alloy ribs. Both planes carried ailerons and there were automatic slots on the upper one. The lower wing was cranked, with negative dihedral over a short centre section, and the main undercarriage legs joined the wing at the end of this section. The main undercarriage was split, a necessary feature in a torpedo bomber carrying its long weapon under its fuselage; there was a small tailwheel. The tailplane was externally braced and both elevators and rudder were balanced. The square-section fuselage was of steel tube construction, aluminium covered at the front and canvas covered at the rear, and filled the space between the wings, deep enough for a spacious, windowed cabin for the observer/navigator. This cabin was between both the wings and the two cockpits; the pilot sat forward of the upper wing, with his head above it and the gunner's position was well aft of the trailing edge. The latter had a ring-mounted .303 in Lewis machine gun, and there was an unusual metal tunnel that could be slid rearwards to protect him from the elements when the gun was not in use. There was also a single, forward-firing .303 in Vickers machine gun operated by the pilot. The fuselage diameter decreased to the engine mounting, holding a supercharged 810 h.p. Armstrong Siddeley Tiger IV in a long chord cowling.

A.W.19 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
49 ft 8 in	42 ft 2 in	13 ft	654 sq ft	4298 lb	19290 lb		163 mph/ 142 kn		21000 ft
15.14 m	12.85 m	3.96 m	60.76 m2	1950 kg	8750 kg		262 km/h		6401 m

Low wing monoplane bomber/transport with a crew of four and capacity for 24 troops, to Specification C.26/31 to meet the requirements of OR.4. It had a fabric covered braced steel fuselage accommodating a large cabin to fulfil its primary transport role but with room for internal bomb racks under the cabin floor, with provision for 2,000 lb of bombs. The wings used a novel structure, patented by Armstrong Whitworth, of a massive light alloy box-spar braced internally with steel tubes. This structure was extremely strong but required a thick wing section, increasing drag. Twin fins and rudders were mounted on a low set strut braced horizontail tailplane. It was the first Armstrong Whitworth Aircraft to be fitted with a retractable undercarriage, the two independent single wheel units being folded by hydraulic power upwards and forwards into the engine nacelles. Defensive armament consisted of single machine guns in nose and tail turrets. Two 810 h.p. Armstrong Siddeley Tiger VI powerplants.

A.W.23 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
88 ft	80 ft	19 ft 6 in	1308 sq ft		24100 lb		162 mph/ 141 kn	790 mi	18100 ft
26.82 m	24.38 m	5.94 m	121.52 m2		10932 kg		261 km/h	1271 km	5517 m

Two seat mid-wing cantilever monoplane long range day bomber to Specification P.27/32 to meet the requirements of OR.7. Its front fuselage was a welded tubular steel structure, and the rear fuselage a monocoque light alloy with an unbraced tailplane, fin and rudder. The conventional landing gear was hydraulically retractable by either an engine-driven or hand pump leaving the tyres partially exposed. The pilot was seated ahead of the wing leading edge and the gunner/observer in a distant cockpit aft of the spar enclosed in a hand-operated turret. The aft cockpit could be fitted with a second set of controls for flight training. The single 870 h.p. Armstrong Siddeley Tiger VIII powerplant was housed in a long-chord cowled and drove a three-bladed propeller.

A.W.29 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
49 ft 10 in	43 ft 10 in	13 ft 3 in	412 sq ft		9000 lb	208 mph/ 181 kn	225 mph/ 196 kn	1200 mi	21000 ft
15.19 m	13.36 m	4.04 m	38.28 m2		4082 kg	335 km/h	362 km/h	1931 km	6401 m

Two seat twin engined monoplane turret fighter to Specification F.5/33. The fuselage was of light alloy monocoque construction, with the pilot located in a fully enclosed cockpit above the leading edge of the wing. Armament consisted of a single nose turret with twin Lewis machine guns, plus two wing mounted Vickers machine guns, operated by the pilot. The specification was superceded by F.9/34 (see below). Two 550 h.p. Armstrong Siddeley Terrier powerplants.

A.W.34 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
47 ft	37 ft 6 in				6100 lb		261 mph/ 227 kn
14.33 m	11.43 m				2767 kg		420 km/h

Twin engined heavy bomber to Specification B.1/35. An A.W.38 Whitley development with two, partially buried, Rolls-Royce Merlin powerplants in streamlined nacelles. Defensive armament was increased by the introduction of a mid upper turret and offensive armament increased to 5000 lb of bombs.

A.W.39 Specification (performance estimated)
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
84 ft	71 ft 6 in				23950 lb		260 mph/ 226 kn
25.6 m	21.79 m				10864 kg		418 km/h

Two seat twin engined monoplane turret fighter to Specification F.9/35, a development of the A.W.34. The tapered wing featured an unswept leading leading edge. Wing construction was to have featured a light alloy main box spar with, the wing being skinned in light alloy back to the rear spar, then fabric aft of that. The narrow all metal fuselage housed the pilot in an enclosed cockpit forward of the leading edge, the turret, with it's 4 .303 machine guns, being located just forward of the trailing edge.Mainwheels retracted rearwards into the wing mounted engine nacellesTwo 550 h.p. Armstrong Siddeley Terrier powerplants.

F.9/35 Specification (as of February 1937 - performance estimated)
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
39 ft	37 ft 3 in		295 sq ft		6700 lb		328 mph/ 285 kn
11.89 m	11.35 m		27.41 m2		3039 kg		528 km/h

Single seat, 60 degree swept wing, transonic flight research aircraft to Specification E.16/49, with an all moving variable incidence tail mounted high on the fin. The wing had a drooped leading edge and elevons. The proposed fighter variant was larger at 51 ft 2 in long and 27 ft span, and featured a housing for a radar scanner well inside the nose intake. One Armstrong Siddeley Sapphire or Rolls-Royce Avon powerplant.
The aircraft was later redesigned, firstly, with a wing featuring a cranked leading edge and later with a delta wing featuring high mounted tailplane.

A.W.58 Specification (60 degee swept wing)
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
24 ft	45 ft 2 in		190 sq ft		12000 lb		Mach 1.07
7.32 m	13.77 m		17.65 m2		5443 kg