Renault 4P / Bengali 4
Charles Lindbergh's Atlantic Ocean crossing in 1927 inspired Renault to enter the light aero-engine market to diversify the range of engines they offered. The resulting Renault 4Ps, aka Renault Bengali 4, with 115 mm (4.5 in) bore and 140 mm (5.5 in) stroke, delivered 95 hp (71 kW) and proved popular, later versions powering several record-breaking light aircraft with up to 150 hp (110 kW).
Developed by Charles-Edmond Serre, by 1931 the 6.3-litre 4Pdi had evolved to give 110 hp (82 kW) to 120 hp (89 kW), with the adoption of 120 mm (4.7 in) bore steel cylinder liners, aluminium alloy cylinder heads attached by long studs to the crankcase, Duralumin connecting rods and magnesium alloy crankcase.
In 1946 production of the Renault 4P-01 resumed at the SNECMA factory at Arnage, until 1949, with at least 762 engines manufactured.
The initial version with 115 mm (4.5 in) bore and 140 mm (5.5 in) stroke, delivered 95 hp (71 kW)
95hp / 135kg - Caudron Luciole
Inverted development of the Pb retaining the 115 mm (4.5 in) bore
Further development of the Ps retaining the 115 mm (4.5 in) bore
Inverted, introduced 120 mm (4.7 in) bore steel cylinder liners, aluminium alloy cylinder heads attached by long studs to the crankcase, Duralumin connecting rods and magnesium alloy crankcase. 110 hp / 150 kg - Hanriot 16, 120 hp / 155 kg - Caudron Phalène
Inverted, rated at 150 hp (110 kW) for take-off, the 4Pei entered production before WWII
Inverted lower rated version, giving 105 hp (78 kW) for take-off, using 73-octane fuel.
140 hp (100 kW) with fuel injection.
Postwar production version of the 4Pei, rated at 145 hp (108 kW) for take-off.
As the 4P-01 but with an inverted flight Zenith carburettor
As for the 4P-03 but with a modified oil system
As for the 4P-03 but with a modified carburettor
Licence production of a 152hp Renault 4P variant.
ANF Les Mureaux 160T
Caudron C.270 Luciole
Caudron C.280 Phalène
Caudron C.480 Frégate
Caudron C.510 Pelican
Max Holste MH.52
Stampe et Vertongen SV-4B
Type: 4-cylinder naturally aspirated air-cooled inverted in-line piston aircraft engine
Bore: 120 mm (4.7 in)
Stroke: 140 mm (5.5 in)
Displacement: 6.3 L (380 cu in)
Length: 1,729 mm
Width: 480 mm
Height: 708 mm
Dry weight: 147 kg
Valvetrain: Pushrod-actuated, single intake and single exhaust valve per cylinder
Fuel system: 1x Zenith 601GS down-draught carburettor
Fuel type: 80 Octane petrol
Oil system: Pressure fed, 3.0 kg/sq.cm (43 lbf/sq.in), dry sump
Cooling system: Air
145 hp (108 kW) at 2,450 rpm @ take-off
140 hp (100 kW) at 2,400 rpm @ sea-level normal
110 hp (82 kW) at 2,200 rpm @ sea-level cruise
Specific power: 17.15 kW/L (0.38 hp/cu.in)
Compression ratio: 5.8:1
Specific fuel consumption: 0.186 kg/kW/hr
Oil consumption: 0.005 kg/kW/hr
Power-to-weight ratio: 0.74 kW/kg