Argus As 411

As 411
	Preserved Argus As 411
Type	Piston aircraft engine
Manufacturer	Argus Motoren
Major applications	Arado Ar 96; Focke-Wulf Fw 189
Number built	2,600
Developed from	Argus As 410

The Argus 411 was an air-cooled, inverted-V12 aircraft engine developed by Argus Motoren in Germany during World War II.^[1]

Design and development

The As 411 was a refined and more powerful version of the Argus As 410. Most 411 production was undertaken by Renault in occupied Paris, these engines were used to power the Siebel Si 204 and the postwar Dassault MD 315 Flamant. It developed 600 PS (592 hp, 441 kW) at 3,300 rpm

Following the end of World War II, Renault continued to manufacture the engine as the Renault 12S. After the merger of the French aircraft engine manufacturers into SNECMA in 1945, production continued under the new designation SNECMA 12S.

Variants

Argus As 411A in Deutsches Museum München

As 411: A refined and more powerful version of the Argus As 410.
Renault 12S: Production of the As 411 after World War II in France.
SNECMA 12S: (a.k.a. SNECMA Renault 12S) Designation change on the formation of SNECMA.
SNECMA 12T: (a.k.a. SNECMA Renault 12T) Refined version of the 12S with new pistons, cylinders and revised induction system.
SNECMA 12T-303: Dassault propeller
SNECMA 12T-312: Ratier propeller

Applications

Specifications (SNECMA 12S)

Data from Aircraft engines of the World 1953 ^[2]

General characteristics

Type: 12-cylinder inverted 60-degree Vee
Bore: 105 mm (4.1 in)
Stroke: 115 mm (4.5 in)
Displacement: 12 L (730 cu in)
Length: 1,620 mm (64 in)
Width: 700 mm (28 in)
Height: 992 mm (39.1 in)
Dry weight: 369 kg (814 lb)

Components

Valvetrain: One exhaust and one inlet valve per cylinder, push-rod operated.
Supercharger: Gear driven centrifugal supercharger, 9.25:1 drive ratio.
Fuel system: 1x Bronzavia 92-195A1 updraught carburetor with automatic boost and altitude control.
Fuel type: 100/130 Aviation gasoline
Oil system: Pressure fed 3.9 bar (57 psi)
Cooling system: Air-cooled
Reduction gear: Planetary reduction gear: 0.572:1
Air equipment 50-920 electric inertia starter

Performance

Power output:

Take-off:450 kW (600 hp) at 3,300 rpm / 1,325 mmHg (52.2 inHg) +5.0 kg (11.1 lb) boost

Normal:330 kW (440 hp) at 3,250 rpm at 2,400 m (7,900 ft)

Cruising, max:260 kW (350 hp) at 3,100 rpm at 2,600 m (8,500 ft)

Specific power: 37 kW/L (0.82 hp/cu in)
Compression ratio: 6.4:1
Specific fuel consumption: 0.30 kg/kWh (0.5 lb/(hp⋅h))
Oil consumption: 0.013 kg/kWh (0.022 lb/(hp⋅h))
Power-to-weight ratio: 0.83 kg/kW (1.36 lb/hp)
BMEP 13.6 bar (197 psi)

References

^ Gunston, Bill (1989). World Encyclopaedia of Aero Engines (2nd ed.). Cambridge, England: Patrick Stephens Limited. p. 16. ISBN 978-1-85260-163-8.
^ Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 296–297.