Franklin O-540

O-540/8AC
Type	Piston aircraft engine
National origin	United States
Manufacturer	Franklin Engine Company
First run	1942

The Franklin O-540 (company designation 8AC) was an American air-cooled aircraft engine that first ran in the early-1940s. The engine was of eight-cylinder, horizontally-opposed layout and displaced 540 cu in (9 L). The power output was nominally 300 hp (224 kW).

Variants

8ACG-538 (XO-540-1): Geared propeller drive at 0.632:1, 300 hp (224 kW) at 3,200 rpm

8ACSA-538 (XO-540-7): Supercharged, 300 hp (224 kW)

8ACGSA-538 (XO-540-3/O-540-5): Supercharged and geared,330 hp (246 kW) at 3,200 rpm

Applications

Northrop N-9M

Specifications (8ACG-538/XO-540-1)

Data from ^{[citation needed]}

General characteristics

Type: 8-cylinder air-cooled horizontally opposed aircraft piston engine
Bore: 4.625 in (117.5 mm)
Stroke: 4.0 in (101.6 mm)
Displacement: 537.6 in³ (8.8 L)
Dry weight: 438 lb (199 kg)

Components

Cooling system: Air-cooled

Performance

Power output: 300 hp (224 kW) at 3,200 rpm

References

Notes

Bibliography

Gunston, Bill. (1986) World Encyclopedia of Aero Engines. Patrick Stephens: Wellingborough. p. 57

Franklin aircraft engines

By displacement

Two-cylinder engines

By displacement	O-110 O-120
By company designation	2A-110 2A-120 2A4-45 2A4-49 2AL-112

Four-cylinder engines

By displacement	O-150 O-170 O-175 O-180 O-200 O-225 O-235
By company designation	4A-225 4A-235 4A4-100 4A4-75 4A4-85 4A4-95 4AC-150 4AC-171 4AC-176 4AC-199 4ACG-176 4AL-225 Sport 4

Six-cylinder engines

By displacement	O-265 O-300 O-315 O-335 O-350 O-405 O-425 O-500
By company designation	6A-335 6A-350 6A3 6A4 6A8-215 6AC-264 6AC-298 6AC-403 6ACV-245 6AG-335 6AG4-185 6AG6-245 6AGS-335 6AGS6-245 6AL-315 6AL-335 6AL-500 6ALV-335 6AS-335 6V-335 6V4 6V6-245-B16F 6V6-245 6V6-300-D16FT 6V6-300 6VS-335

Eight-cylinder engines

By displacement	O-400 O-540
By company designation	8AC-398 8ACG-398 8ACG-538 8ACGSA-538 8ACSA-538

12-cylinder engines

By displacement	O-595 O-805
By company designation	12AC-596 12AC-806

v t e United States military piston aircraft engine designation system
H (four-bank H-configuration inline)	H-1640 XH-2240 XH-2470 XH-2600 XH-3130 XH-3730 H-4070
IV (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-1150 V-1237 V-1400 V-1440 V-1460 V-1510 V-1560 V-1570 V-1650 (P) V-1710 V-1950 V-3420
V (inverted-V inline)	V-770 V-1650 (L)
VG (inverted-V inline)	VG-1410
W (three-bank W-configuration inline)	W-2779
See also: X-1800 US military gas turbine aeroengines Piston engine configurations

This page was last edited on 24 July 2021, at 10:01

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