Kinner B-5
| B-5 | |
|---|---|
| |
| A Kinner B-5 on display at the Old Rhinebeck Aerodrome in New York, as used in their Fleet Finch biplane. | |
| Type | Radial engine |
| Manufacturer | Kinner Airplane & Motor Corporation |
| Developed from | Kinner K-5 |
| Developed into | Kinner R-5 |
The Kinner B-5 was a popular five cylinder American radial engine for light general and sport aircraft of the 1930s.
Design and development
The B-5 was a development of the earlier K-5 with slightly greater power and dimensions. The main change was the increase in cylinder bore from 108 mm (4.25 in) to 117 mm (4.625 in) and a corresponding increase in displacement from 372 cu in (6.1 liters ) to 441 cu in (7.2 liters ). One difference the B-5 had from radial engines of other manufacturers was that each individual cylinder had its own camshaft, a system also used by the contemporary Soviet-built, 8.6 litre-displacement Shvetsov M-11 five cylinder radial, while most other radial engine designs used a "cam ring" for the same purpose, connected to every cylinder's valves. The B-5 was a rough running but reliable engine. The B-5 and its derivatives were produced in the thousands, powering many World War II trainer aircraft; its military designation was R-440. The B-5 was followed by the R-5 and R-55.
Applications
- Fleet Fawn
- Fleet Finch
- Kinner Sportster
- Kinner Sportwing
- Lincoln AP
- Monocoupe 125
- Redfern DH-2
- Ryan PT-22 Recruit
- Savoia-Marchetti S.56
Specifications (Kinner B-5)
Data from Jane's all the World's Aircraft 1938[1]
General characteristics
- Type: Five-cylinder, air-cooled, radial
- Bore: 4.625 in (117.5 mm)
- Stroke: 5.25 in (133 mm)
- Displacement: 441 cu in (7.23 L)
- Length: 32.325 in (821.1 mm)
- Diameter: 45.375 in (1,152.5 mm)
- Dry weight: 295 lb (134 kg)
Components
- Valvetrain: 1 Inlet and 1 Exhaust valve per cylinder, individual camshafts for each cylinder
- Fuel system: 1x Holley or Stromberg Carburetor
- Fuel type: 73 Octane
- Oil system: Circulating dry sump system
- Cooling system: Air-cooled
Performance
- Power output: 125 hp (93 kW) at 1,925 rpm max; 89 hp (66 kW) at 1,725 rpm cruise
- Compression ratio: 5.25:1
- Specific fuel consumption: 0.60 lb/hp hr (0.365 kg/kw hr)
- Oil consumption: 0.025 lb/hp hr (0.0152 kg/kw hr)
- Power-to-weight ratio: 0.42 hp/lb at cruise
See also
Related development
Comparable engines
Related lists
References
- ^ Grey, C.G.; Bridgman, Leonard, eds. (1938). Jane's all the World's Aircraft 1938. London: Sampson Low, Marston & company, ltd. p. 88d.
Further reading
- Gunston, Bill (1986). World Encyclopedia of Aero Engines. Newton Abbot: Patrick Stephens. pp. 99–100.