Napier Lion

Napier Lion II

Early in the First World War Napier were contracted to build aero engines to designs from other companies: initially a Royal Aircraft Factory model and then Sunbeams. Both proved to be rather unreliable, and in 1916 Napier decided to design their own instead. Reasoning that the key design criteria were high power, light weight, and low frontal area, the engine was laid out with its 12 cylinders in what they called a “broad arrow”—three banks of four cylinders sharing a common crankcase. This suggested the design’s first name, the Triple-Four. These designs are sometimes referred to as a W-block, although that designation applies more correctly to an engine in which a common crankcase is shared by not merely three but in fact four rows of cylinders (since a “W” is made of four lines or bars). The engine was also advanced in form, the heads using four valves per cylinder with twin overhead camshafts on each bank of cylinders and a single block being milled from aluminium instead of the more common separate-cylinder steel construction used on almost all other designs.

Under A. J. Rowledge, the design of the newly renamed Lion was completed in 1917, and the first hand-built prototypes ran later that year. It was fitted to a de Havilland built DH.9 in early 1918, proving to have many cooling problems. In addition the milled block turned out to be difficult to build with any accuracy and they reverted to separate cylinders, although they remained aluminium. Both of these problems were worked out by the middle of the year and the engine entered production in June 1918. The first Lion I versions delivered 450 hp (335 kW) from their 24 litres. As the most powerful engine available (particularly after a turbocharger became an option in 1922), the Lion went on to be a huge commercial success. Through the years between the wars Napier manufactured little else. Between the wars it powered over 160 different types of aircraft.

In highly-tuned racing versions the engine could reach 1,300 hp (970 kW), and it was used to break many world records: height, air speed, and distance in aircraft, boats, delivering 1,375 hp (1,025 kW) in a highly tuned Lion for a water speed record of 100 mph (160 km/h) in 1933. In land speed records, Lion engines powered many of Sir Malcolm Campbell’s record breakers including a record of over 250 mph (400 km/h) in 1932 and John Cobb’s 394 mph (634 km/h) Railton Mobil Special in 1947 – a record that came well after the Lion had passed its prime and stood until the 1960s. The record had been held by British drivers for 32 years. Lions powered successful entrants in air racing, the Schneider Cup, in 1922 and 1927, but were then dropped by Supermarine in favour of a new engine from Rolls-Royce, the Rolls-Royce R which had been especially designed for racing. It was a Lion that powered the Supermarine S5 that won the 1927 Schneider Trophy for seaplane speed racing.

It was still being fitted to planes in 1929 and it was still being put into boats in 1933.

During the 1930s a new generation of much larger and more powerful engines started to appear, and the Lion was clearly past its prime. Gradually, they fell further and further behind. By the time the Bristol Hercules and the Rolls-Royce Merlin arrived in the late 1930s, the Lion was too small and old-fashioned.

A marine version of the Lion, unsurprisingly called the Sea Lion, was used to power high speed air-sea rescue launches operated by the RAF.

Another adaptation for the Lion aero engine was propeller-driven motor sleighs, which were used for high-speed transport and SAR duties on sea ice by the Finnish Air Force and Navy.

Napier Lion W12

Lion models:

Lion I
1918
450 bhp (340 kW) at 1,950 rpm
geared, also related IA and 1AY

Lion II
1919
Works No: E64
450 bhp (340 kW) at 2,000 rpm

Lion IIII
experimental geared
Gloster Gorcock

Lion V
470 bhp (350 kW) at 2,000 rpm
500 bhp (370 kW) at 2,250 rpm
VA had increased CR to 5.8
Mainstay engine of the RAF in the late 1920s, replaced by Lion XI

Lion VS
Works No: E79
Turbocharged, intercooled

Lion VIS
1927
Turbocharged
Application: Gloster Guan

Lion VII
1925
700 bhp (520 kW) (racing)
Application: Gloster III (Schneider Trophy entrant)
Supermarine S.4

Lion VIIA
1927
Works No: E86
900 bhp (670 kW) (racing)
Application: Golden Arrow
Blue Bird (1927)
Miss England I
Supermarine S.5
Gloster IV

Lion VIIB
1927
875 bhp (652 kW) (racing)
geared
Application: Supermarine S.5
Gloster IV

Lion VIID
1929
Works No: E91
1,350 bhp (1,010 kW) at 3,600 rpm (racing)
Supercharged, about 6-8 built
Application: Blue Bird (1931)
Fred H Stewarts Enterprise
Betty Carstairss Estelle V powerboat
Miss Britain III
Gloster VI (Schneider Trophy entrant)
Railton Special (John Cobb’s land speed record car)

Lion VIII
1927
direct drive
Gloster Gorcock

Lion XIA
1928
580 bhp (430 kW) at 2,585 rpm, 6:1 CR
RAF production model
Application: Napier-Railton

Lioness
Works No: E71
Inverted layout, for better visibility. At least some were built turbocharged, for racing.

Sea Lion
1933
500 and 600 bhp (370 and 450 kW)
Marine version of Lion XI
British Power Boat Company Type Two 63 ft HSL

Applications:
Aircraft
Alliance P.2 Seabird
Avro Bison
Blackburn Blackburn
Blackburn Dart
Blackburn Pellet
Blackburn Ripon
Blackburn Velos
Boulton Paul Atlantic
Boulton Paul Bodmin
Boulton Paul Bolton
English Electric Kingston flying boat (prototype)
Fairey III
Fairey Fawn
Fokker C.IV-W
Fokker C.V
Fokker D.C.I
Fokker D.XIII
Gloster Gorcock
Gloster Guan
Handley Page H.P.31 Harrow
Handley Page Hyderabad
Mitsubishi B1M
Parnall Pike
Parnall Possum
Parnall Puffin
Supermarine S.4
Supermarine S.5
Supermarine Seagull
Supermarine Southampton
Tarrant Tabor
Vickers Vernon
Vickers Valparaiso
Vickers Victoria
Vickers Virginia
Vickers Vixen
Westland Walrus

Other applications
British Power Boat Company Type Two 63 ft HSL
British Power Boat Company 60 ft 4 in

Specifications:
Lion II
Type: 12-cylinder water-cooled W-block (3 banks of 4 cylinders) aircraft piston engine
Bore: 5.5 in (139.7 mm)
Stroke: 5.125 in (130.17 mm)
Displacement: 1,461.6 cu.in (23.9 L)
Length: 57.5 in (1460 mm)
Width: 42.0 in (1067 mm)
Height: 43.5 in (1105 mm)
Dry weight: 960 lb (435 kg)
Valvetrain: Two intake and two exhaust valves per cylinder actuated via double overhead camshafts per cylinder block.
Cooling system: Water-cooled
Power output: 480 hp (358 kW) at 2,200 rpm at 5,000 ft
Specific power: 0.32 hp/cu.in (15.0 kW/L)
Compression ratio: 5.8:1
Power-to-weight ratio: 0.5 hp/lb (0.82 kW/kg)

Napier

By 1931, during the Great Depression, Bentley was having financial difficulties. When funds ran out in 1931, the receivers were negotiating with D.Napier & Sons Ltd for the sale of the remains of Bentley. However, Rolls-Royce put in a secret bid through a Liechtenstein company, and secured Bentley Motors for £125,256. For this, Rolls-Royce got the factory equipment, a number of incomplete car chassis, and the services of Walter Bentley for three years.

Nando Groppino

Now considered a classic of Italian ultra-lights, the Groppino is the basic for excellence, for the school and who that want an economic ultralight aircraft, simple and fun. The aircraft is equipped with dual controls and nose wheel steering.

Stall: 26 kt / 30 mph / 48 kmh
Cruise: 46 kt / 53 mph / 85 kmh
VNE: 73 kt / 84 mph / 135 kmh
Empty Weight: 195 kg / 430 lbs
MTOW Weight: 450 kg / 992 lbs

Nando Flotta Sport Cruiser

The cockpit offers great visibility and the aircraft is constructed entirely of metal. The aircraft engine is a very sturdy and reliable Rotax 912 ULS so you can travel at a cruising speed of 125 mph (201 km / h) with a fuel consumption of around 17 liters / h.
Price 2009: 61900 EURO

Stall: 30 kt / 34 mph / 55 kmh
Cruise: 109 kt / 125 mph / 201 kmh
VNE: 131 kt / 151 mph / 243 kmh
Climb Ratio: 1200 ft/min / 6 m/s
Take-off distance (50ft obstacle): 360 ft / 110 m
Landing distance (50ft obstacle): 400 ft / 122 m

Nando Trial

Foldable wings, all metal frame construction with central chrome molybdenum. Large door on right side that allows easy access to front and rear seat. Tundra wheels equipped to operate on rough terrain.
The Jabiru engine ensures efficient and low noise while maintaining excellent performance.

Stall: 32 kt / 37 mph / 60 kmh
Cruise: 86 kt / 99 mph / 160 kmh
VNE: 119 kt / 137 mph / 220 kmh
Empty Weight: 285 kg / 628 lbs
MTOW Weight: 450 kg / 992 lbs
Take-off distance (50ft obstacle): 390 ft / 120 m
Landing distance (50ft obstacle): 330 ft / 100 m

Engine: Rotax 503, 52 hp
Wing span: 9.9 m
Wing area: 16.7 sq.m
MAUW: 450 kg
Empty weight: 180 kg
Fuel capacity: 30 lt
Max speed: 120 kph
Cruise speed: 80 kph
Minimum speed: 45 kph
Climb rate: 4 m/s
Seats: 2
Fuel consumption: 15 lt/hr

Nanchang N5A

In 1988 Textron was contracted to supply three 400hp IO-720-D1B engines for the N-5. The contract provided for three specially equipped engines to be supplied for the N-5 prototypes, with an option on production engines from late-1990.

Nanchang developed the N-5A agricultural aircraft, first flown on 26 December 1989.
The N5A received its CAAC production certificate in the 1990s. By 1995, eight had been built.

Engine: Lycoming IO-720-D1B

Nanchang Q-6

In the mid-’70s, China managed to get their hands onto Egyptian MiG-23BNs and -MSs, and downed American F-111s. Using this captured technology, Nanchang was asked to develop a swing-wing strike aircraft for the PLAAF. Originally, plans centered around a quick domestic copy of the MiG-23BN. However, when PLAAF requirements added air-to-air capabilities, the MiG-23BN would prove inadequate. Plans then shifted to repurposing the F-111 electronics for the new design. Chinese industry proved incapable of producing systems as small as the design called for, forcing a major redesign that made the Q-6 comparable in size to the Su-24. The side intakes of the MiG-23 proved inadequate for dogfighting, so they were relocated to the chin, while the inadequate engine was to be replaced with the domestically-produced WS-6 turbofan. Overall, however, the project quickly proved to be beyond the means of the Chinese aerospace industry. Development dragged on as much of the intended onboard systems proved too difficult to copy. While an advanced fly-by-wire system (first of its kind for China) was developed for the Q-6’s swing wings, it proved to be 12% heavier than the one employed on the MiG-23. The WS-6 proved to be failure as well, and thus, in 1989, with requirements shifting away from swing-wing designs, the Q-6 was finally cancelled.