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The Take Off TBM 12 is an aircraft engine, ... It employs electronic ignition and produces 115 hp (86 kW) at 7200 rpm, with a compression ratio of 13.1:1. [1]
Max takeoff weight: 5,000 kg (11,023 lb) Fuel capacity: 1,050 L (277 US gal; 231 imp gal) Powerplant: 2 × Bristol Mercury VIII 9-cylinder air-cooled radial piston engines, 540 kW (730 hp) each at 2,650 rpm - takeoff power
The M-63 was an improved version of the M-62 with the power output increased to 821 kW (1,100 hp) at 2,300 rpm for takeoff and 671 kW (900 hp) at 2,200 rpm at 4,500 m (14,800 ft) due to a higher compression ratio of 7.2:1 and a higher redline.
It employs dual electronic ignition and produces 160 hp (119 kW) at 5800 rpm for takeoff and 137 hp (102 kW) at 5500 rpm continuous operation, with a maximum operating altitude of 23,000 ft (7,010 m). [1]
O-580-1 Military variant similar to the GSO-580-D [citation needed] GSO-580 Eight-cylinder, horizontally opposed, geared-drive, supercharged, 578 cubic inches (9.47 litres), 375 hp (280 kW) at 3300 rpm for take-off, 320 hp (239 kW) at 3000 rpm continuous, dry weight 619 lb (281 kg), Bendix PSH-9BDE carburetor.
The propeller has four rotational speed settings: 655, 730, 842 and 860 rpm. [11] The 655 rpm setting is for low-altitude cruise, 730 rpm for normal cruise, and 842 rpm for takeoff and special maneuvers. [16] The propeller converts the engine power into 110 kN (11,000 kgf; 25,000 lbf) of thrust. [41]
215 hp (160 kW) at 2,800 rpm The C2 is the same as C1, except for the induction system piping. When a Marvel Schebler MA4-5 carburetor is used on the 6A-350-C1 engine for improved acceleration the takeoff and max. continuous rating are 215 hp (160 kW) at 2,800 rpm. [1] [2] 6AS-350 Turbocharged, 235 hp (175 kW) at 2,800 rpm. 6V-350
The Pegasus was the same size, displacement and general steel/aluminium construction as the Jupiter, but various improvements allowed the maximum engine speed to be increased from 1,950 to 2,600 rpm for take-off power.