BMW 801 right The BMW 801 was a powerful German air-cooled radial aircraft engine built by BMW and used in a number of German military aircraft of World War II. The engine’s cylinders were in two rows of seven cylinders each, the bore and stroke were both 156 mm, giving a total capacity of 41.8 litres (2,562 in³). The engine generated between 1,600 and 2,000 hp (1,200 and 1,500 kW). The unit (including mounts) weighed around 1,250 kg and was about 1.27 m across, depending on the model. The engine was developed from the experience gained when BMW had been manufacturing Pratt & Whitney Hornet engines under license as the BMW 114 in the 1930s. They introduced an improved version as the BMW 132, which was fairly successful during the mid-30s. In 1935 the RLM funded prototypes of two much larger radial designs, one from Bramo, and another from BMW. BMW bought Bramo soon after the projects started; unsurprisingly BMW folded the Bramo engineers into their existing project, cancelling the Bramo design. The resulting proposal was a two-row version of the 132, the 1,400 hp (1,000 kW) BMW 139. The 139 was originally intended to be used in similar roles as the other German radials, namely bombers and transport aircraft, but mid-way through the program Kurt Tank suggested it for use in the Focke-Wulf Fw 190 fighter project. Radial engines were rare in land-based fighters at the time due to their larger frontal size, but Tank felt that attention to detail could result in a streamlined radial that would not suffer undue drag. His solution for the 139 was to use an engine-driven fan behind an oversized prop-spinner, which blew air through the engine, with some being "sucked" through S-shaped ducts over a radiator for oil cooling. However this system proved almost impossible to make work with the 139, and as the engine was already fairly dated in terms of design, and in 1938 BMW proposed an entirely new engine that could be brought to production quickly. Work started in October. Differences between the 139 and the new design, named the 801 after BMW was given a new block of engine numbers to use, were fairly minor and limited primarily to details. The 801 retained the 139's older single-valve intake and exhaust for instance, while most engines of the era had moved to four valves per cylinder, or in British use, sleeve valves. Several advances were worked into the design, however, including the use of sodium-cooled valves and a fuel injection system. The supercharger was rather based in the early models, using a single-stage two-speed design directly geared to the engine (unlike the DB 601's hydraulically-clutched version) which led to rather limited altitude performance in keeping with its intended medium-altitude usage. One key advancement was the kommandogeraet (command-device), a hydraulic-electric unit that automatically adjusted engine fuel flow, propeller pitch, supercharger setting, mixture and ignition timing with propeller pitch in response to a single throttle lever, dramatically simplifying engine control. The first 801A's ran in April 1939, only six-months after starting work on the design. The 801B series were identical to the A models, but ran in the opposite direction, turning to the left. They were intended to be used in pairs with the A series on twin-engine designs, thereby cancelling out net torque and making the plane easier to handle. The 801L was an A model modified for "tropical" use. However all of these proved to have terrible cooling problems, and a number of efforts were improvised in an attempt to cure them. All of these were replaced with the C series, which included a new hydraulic prop control, and various changed intended to improve cooling, including cooling "gills" on the cowling behind the engine. With the engine now being used in higher-altitude fighter roles, a number of attempts were made to address the limited performance of the original supercharger. The 801C-1 engines used in the first 190A-1 fighter aircraft delivered about 1,550 hp (1,160 kW) for takeoff, improved to 1,600 hp (1,200 kW) in the 801C-2 used in the 190A-2. These were soon replaced with the 801D series engines, which ran on 96 octane fuel instead of the A/B/C's 87, boosting takeoff power to 1,700 hp (1,270 kW) in the D-1, and 1,730 hp (1,290 kW) in the strengthened D-2. The D models also included a system for injecting a 50-50 water-methanol mixture (known as MW50) into the supercharger output to cool the charge, and thereby reduce backpressure. Although practically every production model 190 included the 801D engine, it was not until very late in the war that the MW50 kits were actually supplied and available. With boosting on, low and medium-altitude performance improved considerably, with takeoff power increasing to 2,000 hp (1,490 kW). The 801G and H models were D engines modified for use in bomber roles, right and left turning, respectively. The 801E was a modification of the D-2 using supercharger gear ratios tuned to higher altitudes. Although takeoff power was unaffected, cruise power increased over 100 hp (75 kW) and "high power" modes for climb and combat were likewise improved by up to 150 hp (110 kW). The E model was also used as the basis for the 801R, which included a much more complex and powerful two-stage four-speed supercharger. Continued improvements to the basic E model led to the 801F, which dramatically improved performance across the board, with takeoff power increasing to 2,400 hp (1,790 kW). It was planned to use the F on all late-model 190's, but the war ended before production started. A number of attempts were made to use turbochargers on the 801 series. The first used a modified 801D to create the 801J, delivering 1,810 hp (1,350 kW) at takeoff and 1,500 hp (1,120 kW) at 40,000 ft (12,200 m), an altitude where the D was struggling to produce 630 hp (470 kW). The 801E was likewise modified to create the 801Q, delivering a superb 1,715 hp (1,280 kW) at 40,000 ft (12,200 m), power ratings no existing allied engine could touch. However none of these engines ever entered production due to high costs, and the various high-altitude designs based on them were forced to turn to other engines entirely, typically the Junkers Jumo 213. Engines were typically delivered from BWM complete in their cowling, ready to be bolted to the front of the plane. This confuses the naming considerably, as they referred to these engines and their "bare" counterparts almost interchangeably. The A, B and L models were known (logically) as the MA, MB and ML in this form, but the common D-2 was instead known as the MG. Later engines were typically referred to with a T in place of the M, however there is little logic to the use of the T; the E model was delivered as the TG or TH, seemingly suggesting a relation to the G and H engines, but in fact those were delivered as the TL and TP. It is rather common to see the turbocharged versions referred to only with the T, notably the TJ and TQ models. Specifications For 801C: Configuration: Two-row, fourteen-cylinder air-cooled radial Bore, Stroke: 156 x 156 mm (6.14 x 6.14 in) Displacement: 41.8 litres (2,562 in³) Compression ratio: 6.5:1 Dimensions: Length: 2006 mm Diameter: 1290 mm Weight: 1055 kg (2325 lb) Power: 1600 hp (1,200 kW) at 2,700 rpm for takeoff SFC: 0.506 lb/hp.h (0.308 kg/kWh) 801A 1,600 hp (1,200 kW) 801D 1,730 hp (1,290 kW) 801S or TS 2,000 hp (1,500 kW) 801F 2,400 hp (1,800 kW), development halted by the end of the war See also List of aircraft engines FAVORITE ARTICLES: History of the World    History of the United States    History of Europe    Ancient History    History    Military History    World War I    Bombing of Dresden    California    US Constitution    Frank Sinatra    Boston    Marbury v. 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