Bristol Coanda Biplanes

Central float two-seater seaplane. It was a single-bay biplane with unswept and unstaggered wings. The circular-section fuselage was mounted between the wings with a gap below and unusual framed struts above at the centre section. The observer's cockpit was between these frames, the pilot sitting at the wing trailing edge, with dual handwheel controls. There was a gap between the upper wing-roots above the front cockpit. The engine was enclosed in a close-fitting aluminium cowling. The fuselage tapered to the tail, which in typical Coandă style comprised a nearly semicircular fixed horizontal stabiliser with a single elevator, plus a balanced rudder without a fixed fin, but an extra rectangular rudder was later added under the tail to offset the keel surface of the main float. There was a single wide mahogany float built by Oscar Gnosspelius, with a pair of water rudders at its rear, but the central float was replaced by a lightweight, purpose-built Consuta float from Saunders and Company of Cowes.Two streamlined cylindrical wingtip floats provided lateral stability. One 80 h.p. Gnome powerplant.

Single-engined, two-seat biplane, with two-bay wings and a slender fuselage, a two bay biplane development of the Coanda Military Monoplane. Early, converted, aircraft used wing warping, with later production aircraft being fitted with ailerons. One 80 h.p. Gnome Lambda powerplant. The designation presumably stood for Tractor Bristol (or Biplane) 80 h.p.

Coanda Type T.B.8 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Endurance	Service Ceiling
37 ft 8 in	29 ft 3 in		450 sq ft	970 lb	1650 lb		70 mph/ 61 kn	5 hrs
11.48 m	8.92 m		41.81 m2	440 kg	748 kg		113 km/h

Type T.B.8 converted to a twin float seaplane using the Gnosspelius float from the Hydro Biplane cut in half. A fixed fin was added, with an additional fin and rudder below the fuselage to counteract the affects of the floats.

Long-range, two-seat biplane, basically consisting of the Coanda Military Monoplane's fuselage, undercarriage and tail unit, fitted with two-bay unstaggered biplane wings. One 70 h.p. Renault powerplant. Originally designated B.R.70 (Bristol Renault 70 h.p.). Also built by Deutsche Bristol-Werke, the German machine featuring extended wings, tapered ailerons, an extra rudder below the tail and a 90 h.p. Daimler-Mercedes powerplant.

Coanda Type B.R.7 Specification - Renault
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Endurance	Service Ceiling
38 ft	27 ft 5 in		440 sq ft	946 lb	1826 lb		63 mph/ 55 kn	5 hrs
11.58 m	8.36 m		40.88 m2	429 kg	828 kg		101 km/h

Coanda Type B.R.7 Specification - Daimler-Mercedes
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Endurance	Service Ceiling
57 ft	27 ft 5 in		570 sq ft	1200 lb	2100 lb		65 mph/ 56 kn	5 hrs
17.37 m	8.36 m		52.95 m2	544 kg	953 kg		105 km/h

Two seat pusher biplane trainer intended as a Boxkite replacement, with equal span wings with ailerons on both the upper and lower wings. The small cockpit had room for two in tandem, although access to the rear seat was restricted by the upper wing. It inherited an unusual four-wheel landing gear from other Coanda designs like the T.B.8. The tail booms were parallel in plan view at a fairly close pitch, the lower booms being continuous with the chassis skids. Initially the nacelle nose shape was a horizontal knife-edge, but as finally built this was changed to a vertical knife-edge.One 80 h.p. Gnome Lambda powerplant fitted at the rear of the cockpit nacelle and driving a pusher propeller. The designation presumably stood for Pusher Bristol (or Biplane) 80 h.p.

Coanda Type P.B.8 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Endurance	Service Ceiling
27 ft 6 in	27 ft 6 in							5 hrs
8.38 m	8.38 m

Single Seat Armoured (S.S.A) biplane, intended to be built by Breguet at Douai, for the French Government. The forward fuselage was built as a monocoque shell built up from sheet steel, colloquially known as 'The Bath', at the Filton works. The armoured shell enclosed the engine, fuel tank, oil tank and cockpit, with the pilot's seat being formed from the shaped rear bulkhead. The engine was fully cowled with sheet steel and drove a two-bladed propeller which had a large sheet steel spinner, perforated to allow cooling air to the rotary engine, and an internal sheet steel cone preventing bullet entry through the cooling holes. The undercarriage consisted of two wheels mounted on struts, with long skids which extended rearwards removing the need for a tail-skid. A feature of the undercarriage requested by the French customer was castering main-wheels allowing cross-wind landings. Attached to the rear end of the armoured tub was a slender rear fuselage which ended with a large balanced rudder, tailplane and elevator. One 80 h.p. Clerget 7Z powerplant.

S.S.A. Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Endurance	Service Ceiling
27 ft 4 in	19 ft 9 in		200 sq ft	913 lb	1200 lb		106 mph/ 92 kn	3 hrs
8.33 m	6.02 m		18.58 m2	414 kg	544 kg		171 km/h

Improved T.B.8. The fuselage was faired above and below and the streamline shape was continued forward by a large hemispherical spinner and cowl enclosing the engine, to which cooling air was admitted by louvers in the spinner. Warping wings were fitted and the tail unit had a fixed vertical fin. Equipment included an electric intercommunication system for the crew. Following initial trials, the spinner was removed, and the wings were rigged with increased stagger to compensate for nose-heaviness. One 75 h.p. Gnome Monosoupape powerplant, later replaced with an 80 h.p. Gnome. The designation presumably stood for Gnome Bristol 75 h.p.

Coanda Type G.B.75 Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Endurance	Service Ceiling
37 ft 8 in	29 ft 3 in							5 hrs
11.48 m	8.92 m