Engines – Power

Renault 4P / Bengali 4

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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.

Variants:
Renault 4Ps
The initial version with 115 mm (4.5 in) bore and 140 mm (5.5 in) stroke, delivered 95 hp (71 kW)

Renault 4Pa

Renault 4Pb
95hp / 135kg – Caudron Luciole

Renault 4Pbi
Inverted development of the Pb retaining the 115 mm (4.5 in) bore

Renault 4Pc
Further development of the Ps retaining the 115 mm (4.5 in) bore

Renault 4Pci
inverted 4Pc

Renault 4Pde

Renault 4Pdi
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

Renault 4Pei
Inverted, rated at 150 hp (110 kW) for take-off, the 4Pei entered production before WWII

Renault 4Pgi
Inverted lower rated version, giving 105 hp (78 kW) for take-off, using 73-octane fuel.

Renault 4Po

Renault 4Poi
140 hp (100 kW) with fuel injection.

Renault 4P-01
Postwar production version of the 4Pei, rated at 145 hp (108 kW) for take-off.

Renault 4P-03
As the 4P-01 but with an inverted flight Zenith carburettor

Renault 4P-05
As for the 4P-03 but with a modified oil system

Renault 4P-07
As for the 4P-03 but with a modified carburettor

Renault MV-4
Licence production of a 152hp Renault 4P variant.

Applications:
ANF Les Mureaux 160T
Aubert Cigale
Boisavia Mercurey
Caudron C.193
Caudron C.232
Caudron C.270 Luciole
Caudron C.280 Phalène
Caudron C.480 Frégate
Caudron C.510 Pelican
Farman F.230
Farman F.281
Farman F.350
Max Holste MH.52
Hanriot LH.16
Hanriot H.180
Morane-Saulnier MS.341
Nord Norécrin
Potez 36/19
SABCA S.40
Stampe et Vertongen SV-4B
Sud-Est SE-2100
Sud-Est SE-2300
Sud-Est SE-2310

Specifications:
Renault 4P-01
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
Power output:
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

Renault 70 hp / Type WB

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The Renault 70 hp or Type WB was a British V-8 aero engine that first ran circa 1913. The engine was manufactured by Renault Limited of West Brompton, London between August 1914 and December 1918, three other companies, including Rolls-Royce, also produced the engine. A variant known as the Type WC used an external oil pump as opposed to the internal pump of the Type WB.

The Renault V-8 engines were noted as inefficient but reliable, the inefficiency being mainly due to the excessively rich fuel/air mixture used to assist cooling. A total of 227 were built.

Applications:
Airco DH.1
Armstrong Whitworth F.K.2
Armstrong Whitworth S.S.27 airship
Blackburn Type E
Bristol B.R.7
Caudron G.3
Central Centaur IVA
Farman MF.7 Longhorn
Farman Shorthorn
Flanders F.4
HMA no.2 airship, short-lived modification
Royal Aircraft Factory B.E.2
Royal Aircraft Factory F.E.2
Royal Aircraft Factory R.E.1
White & Thompson Bognor Bloater

Specifications:
70 hp
Type: Inline air–cooled, upright, 90-degree, V-8 piston engine
Bore: 3.72 in (96 mm)
Stroke: 4.72 in (120 mm)
Displacement: 423.76 cu in (7 L)
Length: 45.5 in (1,156 mm)
Width: 29.8 in (757 mm)
Height: 32.8 in (833 mm)
Dry weight: 396 lb (180 kg)
Valvetrain: Single overhead exhaust valve, single side inlet valve per cylinder
Fuel system: Single carburettor
Fuel type: 40–50 octane petrol
Cooling system: Air-cooled
Reduction gear: 0.5:1, left hand tractor
Power output: 70 hp (52 kW) at 1,750 rpm (takeoff power)
Specific power: 0.17 hp/cu in (7.4 kW/L)
Compression ratio: 4.12:1
Power-to-weight ratio: 0.18 hp/lb (0.28 kW/kg)

Remos REMOS GX / NX

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Remos NXT

Remos of Germany continued in 2012 with three models of its GX line: the GX AVIATOR II, GXnES and GX eLite. A variety of standard features and options include Garmin aera 510 and GPSMAP696, Dynon SkyView EFIS, Dynon D100 and D120 EFIS and much more. 2012 prices range from $120,000 to $145,000, with many options.

GX
Engine: Rotax 912S, 100 hp
Propeller: Sensenich
Gross weight: 1320 lb
Empty weight, std: 670 lb
Useful load, std: 650 lb
Payload, full std. fuel: 518 lb
Fuel capacity: 22 lb
Wingspan: 30 ft. 6 in.
Overall length: 21 ft. 3 in.
Overall height: 7 ft. 5 in.
Wing area: 118 sq. ft
Wing loading: 11.2 lbs./sq. ft
Power loading: 13.2 lbs./hp
Seating capacity: 2
Cabin width: 46.8 in
Vso: 38 kt
Vne: 134 kt
Cruise speed: 113 kt
Max rate of climb: 1050 fpm
Takeoff over 50 ft. obstacle: 730 ft
Landing over 50 ft. obstacle: 760 ft

Remos G-3 Mirage

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The Remos G3 is an FAA approved, German manufactured Light Sport Aircraft. Made mostly of carbon fibre, including the landing gear, the Remos weighs 626 lb empty, leaving a useful load of 695 lb. The cockpit is reinforced with Kevlar. Structural composite wing parts are covered with Ceconite fabric to reduce weight. The strutted wings fold back in 5 minutes.

The Remos G3 is approved to tow gliders up to 625 lb gross and banners up to 1633 sq.ft.

Ailerons and elevator are mass balanced, and there is some rudder surface forward of the hinge. Aileron differential is about 1.5:1. Electric trim and flaps are fitted. Flaps extend to 40 degrees. The fuel tank is high in the aft fuselage. Shoulder width in the cabin is 45.8 in. Doors, which are hinged on top, may be opened in flight to 66 kt. They can be removed before flight.

First flown in 1997, the Remos was introduced in 1998 and proclaimed Aircraft of the year at the biennial AERO sport aviation show in Friedrichshafen, Germany, in 2000.

1998

2007 base price: US$99,500

2008 REMOS G3 AVIATOR II

Gallery

Remos G-3 LSA
Engine: Rotax 912 ULS, 100 hp
TBO: 1500 hr
Prop: 2 blade wood
Fuel type: 100/100LL & auto
Wingspan: 32 ft. 4 in
Overall length: 21 ft. 5 in
Height: 5 ft. 6 in
Wing area: 131 sq. ft
Wing loading: 10.1 lbs./sq. ft
Power loading: 13.2 lbs./hp
Max ramp weight: 1320 lb
Gross weight: 1320 lb
Landing weight: 1320 lb
Empty weight, std: 625 lb
Useful load, std: 695 lb
Payload, full std. fuel: 578 lb
Useful fuel, std: 21 USgals
Seating capacity: 2
Cabin doors: 2
Cabin width: 47 in
VNE: 121 kt / 140 mph / 225 kmh
Cruise speed: 75% power: 113 kt
Vso: 39 kt
Best rate of climb (SL): 1300 fpm / 6.5 m/s
Max operating altitude: 20,000 ft
Takeoff ground roll: 330 ft
Landing ground roll: 590 ft
Take-off distance (50ft obstacle): 450 ft / 137 m
Landing distance (50ft obstacle): 450 ft / 137 m

Engine: Rotax 912, 80 hp
Empty weight: 260 kg
Wing span: 9.8 m
Wing area: 13.31 sq.m
MAUW: 450 kg
Fuel capacity: 60 lt
Max speed: 145 kph
Cruise speed: 140 kph
Minimum speed: 62 kph
Climb rate: 5.8 m/s
Certification: Allemande
Seats: 2
Fuel consumption: 9.5 lt/hr
Price (1998): 114 000 DM

Reissner Ente / Wellblech Ente

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Prof. Dr. Hans Reißner built this canard in the experimental workshop of Junkers that was connected to the “Technische Hochschule Aachen”.

First flying on 23 May, 1912, in second form after having been rebuilt (in the third form, it got four fins under the mainplane).

According to G. Schmitt several versions were built and also flown. The Swiss Robert Gesell presented the machine over a few weeks in Johannisthal at the end of 1912.

Reifschneider Eagle

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A contrivance consisting of two major parts, a cigar-shaped balloon, to which was attached a frame, on which were six propellers. Four propellers were used for ascending and two for steering. The power was supplied by a gasoline engine. The Streator, Illinois inventor declared that his ship could be driven from Chicago to New York at the rate of 100 miles an hour, and that it could be sailed around a tower with its side touching the structure at all times. It was planned to construct the machine at an expense of $ 10,000.