Argus As 8
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The Argus As 8 was a four-cylinder, air-cooled, inverted inline aircraft engine produced in Germany by Argus Motoren in the 1930s.
Variants
As 8A
Initial production version 71 kW (95 hp) maximum for 5 minutes, 60 kW (80 hp) continuous.
As 8B
A more powerful variant developing 101 kW (135 hp) maximum for 5 minutes, 86 kW (115 hp) continuous.
As 8R
A variant produced for sport aircraft, particularly for competition use, developing 110 kW (150 hp) for take-off. Featuring: Increased compression ratio, from 5.36 to 5.8 Improved cooling by increasing the numbers of cooling fins at the cylinder head and the cylinder body Increasing the heat dispersing area of the pistons Improved crankcase and oil cooling Improved cylinder charging Modified valve timing
Applications
- Albatros L 100
- Albatros Al 101
- Arado L II (As 8A)
- Arado L IIa (As 8R)
- Baumgärtl Heliofly III
- BFW M.23
- BFW M.27
- BFW M.29
- BFW M.35
- Blohm & Voss Ha 136
- Comte AC-12 Moskito
- Darmstadt D-22
- DFS 40
- Focke-Wulf Fw 44
- Heinkel He 64
- Heinkel He 72
- Klemm L 25E
- Klemm Kl 32
- Raab-Katzenstein RK.25/32
- Ruhrtaler Ru.3
Specifications (As 8B)
Data from Flugzeug-Typenbuch. Handbuch der deutschen Luftfahrt- und Zubehör-Industrie 1944, Argus AS-8R
General characteristics
- Type: 4-cylinder inverted air-cooled in-line piston engine
- Bore: 120 mm (4.72 in)
- Stroke: 140 mm (5.51 in)
- Displacement: 6.332 L (386.40 cu in)
- Length: 1,075 mm (42.3 in) without airscrew hub
- Width: 470 mm (18.5 in)
- Height: 731 mm (28.8 in)
- Dry weight: 116 kg (256 lb) dry
128.4 kg (283 lb) equipped
Components
- Valvetrain: Overhead valves operated by pushrods and rockers
- Fuel system: One down-draught carburretor
- Fuel type: 80 Octane Aviation gasoline
- Oil system: Pressure feed at 3–6 bar (44–87 psi)
- Cooling system: Air-cooled
Performance
- Power output:
135 PS (133 hp; 99 kW) at 2,200 rpm (5 minutes) at sea level 125 PS (123 hp; 92 kW) at 2,150 rpm (30 minutes) at sea level 115 PS (113 hp; 85 kW) at 2,090 rpm (max continuous) at sea level
- Specific power: 21.3 PS/L (0.344 hp/cu in; 15.7 kW/L)
- Compression ratio: 5.35:1
- Specific fuel consumption:
0.235 kg/PSh (0.53 lb/(hp⋅h); 0.320 kg/kWh) at maximum rpm 0.230 kg/PSh (0.51 lb/(hp⋅h); 0.313 kg/kWh) at maximum continuous rpm
- Oil consumption: 0.008 kg/PSh (0.018 lb/(hp⋅h); 0.011 kg/kWh) at maximum continuous rpm
- Power-to-weight ratio: 1.149 PS/kg (0.514 hp/lb; 0.845 kW/kg)
- B.M.E.P.: 7.7 atm (7.8 bar; 113 psi)
See also
Comparable engines
Related lists
Further reading
Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. p. 15.