Continental R-670

R-670

Continental W670 on display
Type	Piston aircraft engine
Manufacturer	Continental Motors
First run	1934
Major applications	PT-17 Stearman

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 Continental A-70. 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

Ground vehicles

T2 Combat Car
T4 Combat Car
M1 Combat Car
M2 Light Tank
M3 Stuart
LVT-4 Water Buffalo

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

References

Notes

↑ Gunston 1989, p.42.
1 2 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

Wikimedia Commons has media related to Continental R-670.

http://www.oldengine.org/members/diesel/Duxford/usaero1.htm

Continental Motors aircraft engines

Opposed piston engines
(Gasoline)

By company horsepower designation	A40 A50 A65 A75 A80 C75 C85 C90 C115 C125 C140 C145 E165 E185 E225 Tiara series

By displacement	O-170 O-190 O-200 O-205 O-240 O-280 O-300 IO-346 IO-360 IO-368 O-470 O-520 O-526 IO-550

Aircraft Diesel engines

Radial engines

R-670
R-975

Inverted-V engines

XI-1430

Turboprops

TP-500

United States military piston aircraft engine designation system

H (four-bank H-configuration inline)	H-1640 XH-2240 H-2470 XH-2600 XH-3130 XH-3730 H-4070

I (inverted-V inline)	IV-1430 IV-2040 IV-2220

L (single-bank inline)	L-330 L-365 L-375 L-390 L-410 L-440 L-510 L-825

O (opposed)	O-15 O-40 O-45 O-90 O-100 O-145 O-150 O-170 O-175 O-180 O-190 O-200 (C) O-200 (F) O-205 O-235 O-290 O-300 O-335 O-360 (C) O-360 (L) O-405 O-425 O-435 O-470 O-480 O-520 O-540 (F) O-540 (L) O-550 O-580 O-805 O-1230

R (radial)	R-250 R-265 R-270 R-370 (LB) R-370 (K) R-420 R-440 R-500 R-540 (W) R-540 (K) R-545 R-550 R-600 R-670 R-680 R-720 R-755 R-760 R-790 R-830 R-915 R-975 DR-980 R-985 R-1044 R-1300 R-1340 R-1454 R-1510 R-1535 R-1640 R-1670 R-1690 R-1750 R-1820 R-1830 R-1860 R-2000 R-2060 R-2160 R-2180 R-2600 R-2800 R-3350 R-4090 R-4360 XR-7755

V (upright-V inline)	V-720 V-770 V-1150 V-1237 V-1400 V-1410 V-1440 V-1460 V-1510 V-1560 V-1570 V-1650 (L) V-1650 (P) V-1710 V-1950 V-3420

W (three-bank W-configuration inline)	W-2779

See also: X-1800 US military gas turbine aeroengines Piston engine configurations

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