Continental R-670

From Wikipedia, the free encyclopedia
R-670
ContinentalW-670.jpg
Continental W670 on display
Type Piston aircraft engine
Manufacturer Continental Motors
First run 1934
Major applications PT-17 Stearman
M3 Stuart

The Continental R-670 (factory designation W670) was a seven-cylinder four-cycle radial aircraft engine produced by Continental displacing 668 cubic inches (11 litres) and a dry weight of 465 lb (211 kg). Horsepower varied from 210 to 240 at 2,200 rpm. The engine was the successor to Continental's first radial engine, the 170 hp . This engine was used on many aircraft in the 1930s and 1940s. The R-670 was widely used in the PT-17 Stearman primary training aircraft of the U.S. military.[1]

In addition to being used in aircraft, the R-670 was used in a number of light armored vehicles of World War II.

Variants[]

Data from: Jane's All the World's Aircraft 1938[2] Variants of the W670 included:

W670-K
carburetor, 5.4:1 compression, 65 Octane, front exhausts and 225 hp (168 kW)
W670-L
carburetor, 5.4:1 compression, 73 Octane, rear exhausts and 225 hp (168 kW)
W670-M
carburetor, 6.1:1 compression, 80 Octane, front exhausts and 240 hp (179 kW)
W670-N
carburetor, 6.1:1 compression, 80 Octane, rear exhausts and 240 hp (179 kW)
W670-K1
fuel injection, 5.4:1 compression, 73 Octane, front exhausts and 230 hp (172 kW)
W670-L1
fuel injection, 5.4:1 compression, 73 Octane, rear exhausts and 230 hp (172 kW)
W670-M1
fuel injection, 6.1:1 compression, 80 Octane, front exhausts and 250 hp (186 kW)
W670-N1
fuel injection, 6.1:1 compression, 80 Octane, rear exhausts and 250 hp (186 kW)

Applications[]

Aircraft[]

Armored fighting vehicles[]

Specifications (R-670-K)[]

An R-670 fitted to a Boeing Stearman at the Imperial War Museum Duxford

Data from Jane's 1938[2]

General characteristics

  • Type: Seven cylinder air-cooled radial
  • Bore: 5+1⁄8 in (130.2 mm)
  • Stroke: 4+5⁄8 in (117.5 mm)
  • Displacement: 668 cu in (10.95 l)
  • Length: 34+3⁄16 in (868.4 mm)
  • Diameter: 42+1⁄2 in (1,079.5 mm)
  • Dry weight: 450 lb (204.1 kg)

Components

  • Valvetrain: 1 inlet and 1 exhaust valve per cylinder
  • Fuel system: 1 Stromberg NA-R6 Carburetor
  • Fuel type: 65 octane
  • Oil system: Dry sump, one pressure pump, one scavenge pump, enclosed valve-train
  • Cooling system: Air-cooled

Performance

  • Power output: 225 hp (168 kW) at 2,175 rpm
  • Specific power: 0.337 hp/in³
  • Compression ratio: 5.4:1
  • Fuel consumption: 13 US Gal/hr (49 L/hr) at cruising rpm
  • Specific fuel consumption: 0.54 lb/hp/hr (0.328 kg/kW/hr) - at rated rpm
  • Oil consumption: 0.4 US Gal/hr (1.5 L/hr) at cruising rpm
  • Power-to-weight ratio: 0.49 hp/lb at cruising rpm

See also[]

Comparable engines

Related lists

References[]

Notes[]

  1. ^ Gunston 1989, p.42.
  2. ^ a b Jane's All the World's Aircraft 1938. London: Sampson, Low & Martin company Limited. 1938.

Bibliography[]

  • Gunston, Bill. World Encyclopaedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
  • Jane's Fighting Aircraft of World War II. London. Studio Editions Ltd, 1998. ISBN 0-517-67964-7
  • Jane's All the World's Aircraft 1938. London: Sampson, Low & Martin company Limited. 1938.

External links[]

Retrieved from ""