P-39L-1 / IL-2 Sturmovik: Great Battles
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Fighter
P-39L-1
History
Specifications

The most famous American Lend-Lease fighter began development in 1936 as a platform for a powerful 37 mm cannon. Bell later argued that the Airacobra concept was based on three main principles: providing firepower, ease of landing and movement on the ground, and excellent visibility for the pilot. To install powerful weaponry, it was necessary to free up space in the forward section of the fuselage, resulting in a unique aircraft design with the engine located behind the cockpit and its rotation transmitted to the propeller by a long shaft running under the cabin floor.

The project was finally approved in 1938 and the first flight of the prototype took place in April 1939. The experimental, still unarmed aircraft reached a speed of 628 km/h and, as it turned out, had many advantages as well as disadvantages. It had high maneuverability due to the location of the engine near the center of mass and high speed. Thanks to the design of the cockpit and its placement closer to the nose, visibility was excellent. The aircraft proved to be very durable and resisted damage well (except for the tail in the first series of the aircraft). During maintenance, the design of the Airacobra allowed easy access to all parts of the plane, which simplified the work of the technical staff. On the other hand, the plane proved to be very difficult to fly and tended to stall into a flat spin. When bailing out, the pilot could collide with the tail of the aircraft. The Allison engine was installed without a turbocharger, which caused the P-39's performance to deteriorate sharply at high altitudes.

The P-39L-1 was a single-seat, single-engine, all-metal, low-wing cantilever monoplane with a tricycle landing gear and nose wheel. The forward section of the fuselage housed the weapons, the forward gear stowage, and the cockpit. The engine was located behind the cockpit; rotation from the engine to the propeller was transmitted by a 3 m-long shaft. The P-39L-1 differed from the previous series by the installation of an Allison V-1710-63 engine, which developed a takeoff power of 1325 hp.

The pilot's cockpit had a very convenient arrangement of instruments and controls. Entry was through the right cabin door. The left door was not used — the engine control column was on the left side and hindered movement. However, the left door had to be jettisoned in case of an emergency exit from the plane. The pilot was protected in front and behind by bulletproof glass and armor.

These planes were equipped with a nose landing gear with a reinforced fork, which allowed steering at high speeds. To facilitate winter operation, a heating well with an electric heater powered by a ground source was provided in the oil tank. In the left front window of the canopy, a small opening was made through which the pilot could scrape ice from the visor with his hand. The aircraft's armament consisted of a 37 mm cannon in the nose, firing through the hollow propeller shaft, and two synchronized heavy machine guns. Four rifle-caliber machine guns were mounted in the wins. A total of 239 P-39L-1s were built.

In Western Allied aviation, the Airacobra had a bad reputation due to the insufficient altitude of its engine, but on the Soviet-German front, the aircraft's high speed and maneuverability at medium and low altitudes were in demand, where Soviet fighters mainly operated. The most successful Soviet aces flew the P-39: Alexander Pokryshkin, Grigory Rechkalov, Alexander Klubov, Nikolai Gulaev, and the brothers Dmitri and Boris Glinka. In his memoirs, Pokryshkin called the Airacobra his favorite plane because forty-eight of the fifty-nine planes he shot down were in American fighters. To improve the characteristics of the aircraft in the USSR, the wing machine guns were often removed and additional weight was placed in the nose to compensate for excessive rearward tilt. Nearly half of all aircraft produced (4920 units) were delivered to the USSR under Lend-Lease.

Used sources:

1. “American Warplanes of World War II” by David Donald, 1995

2. V. Kotelnikov “Airacobra”. American fighter for Stalin's falcons" 2009

3. Materials from the site airwar.ru

Indicated stall speed in flight configuration: 160..172 km/h
Indicated stall speed in takeoff/landing configuration: 140..151 km/h
 
Dive speed limit: 841 km/h
Maximum load factor: 13.0 G
Stall angle of attack in flight configuration: 18.3 °
Stall angle of attack in landing configuration: 16.3 °
 
Maximum true air speed at sea level, engine mode - Take-off: 539 km/h
Maximum true air speed at 2850 m, engine mode - Take-off: 600 km/h
Maximum true air speed at 4600 m, engine mode - Military: 596 km/h
 
Service ceiling: 9300 m
Climb rate at sea level: 16.7 m/s
Climb rate at 3000 m: 13.5 m/s
Climb rate at 6000 m: 7.2 m/s
 
Maximum performance turn at sea level: 21.5 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 30.3 s, at 270 km/h IAS.
 
Flight endurance at 3000 m: 1.6 h, at 350 km/h IAS.
 
Takeoff speed: 150..180 km/h
Glideslope speed: 180..210 km/h
Landing speed: 155..160 km/h
Landing angle: 17.0 °
 
Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates and turn times are given for Take-off power.
 
Engine:
Model: V-1710-63
Maximum power in War Emergency power mode at sea level: 1550 HP
Maximum power in Take-off mode at sea level: 1325 HP
Maximum power in Military mode at 12000 feet: 1150 HP
Maximum power in Nominal mode at 10800 feet: 1000 HP
 
Engine modes:
Nominal (unlimited time): 2600 RPM, 37.2 inch Hg
Military power (up to 15 minutes): 3000 RPM, 42 inch Hg
Take-off power (up to 5 minutes): 3000 RPM, 51 inch Hg
Maximum Possible power (up to 2 minutes): 3000 RPM, 60 inch Hg
 
Water rated temperature in engine output: 105..115 °C
Water maximum temperature in engine output: 125 °C
Oil rated temperature in engine intake: 60..80 °C
Oil maximum temperature in engine intake: 95 °C
 
Supercharger gear shift altitude: single gear
 
Empty weight: 2929 kg
Minimum weight (no ammo, 10% fuel): 3331 kg
Standart weight: 3508 kg
Maximum takeoff weight: 3868 kg
Fuel load: 326,9 kg / 454 l
Useful load: 939 kg
 
Forward-firing armament:
37 мм cannon "М4", 30 rounds, 150 rounds per minute, nose-mounted
2 x 12,7мм machine gun "M2.50", 200 rounds, 850 rounds per minute, synchronized
4 x 7,62мм machine gun "M2.30", 300 or 1000 rounds, 1350 rounds per minute, wing-mounted
 
Bombs:
104 kg general purpose bomb "FAB-100M"
254 kg general purpose bomb "FAB-250sv"
 
Length: 9.2 m
Wingspan: 10.4 m
Wing surface: 19.82 m²
 
Combat debut: late 1942
 
Operation features:
- There is War Emergency power mode. To engage it, move the throttle to max forward position and set the mxiture control to Full Rich (move it 90% forward to engage the Take-Off mode).
- The engine has a single stage mechanical supercharger which does not require manual control.
- The engine is equipped with an automatic fuel mixture control which maintains optimal mixture if mixture lever is set to Auto Rich (66%) position. To use automatic mixture leaning to reduce fuel consumption during flight it is necessary to set mixture lever to Auto Lean (33%) position. To stop the engine mixture lever should be set to the Cut Off (0%) position. Full Rich positon is used during take-off, in case of emergency or automatic mixture system malfunction.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. Also it is possible to turn off the governor and control propeller pitch manually.
- Water and oil temperatures are controlled manually by adjusting the outlet engine radiator shutters.
- The aircraft has trimmers for all flight-controls: pitch, roll and yaw.
- The aircraft has electrically-actuated landing flaps and they can be extended to any angle up to 43°.
- The nose gear orients by itself, doesn't have brakes and can't be controlled. Its maximum turn angle is 60° left or right.
- The aircraft has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal.
- The aircraft is equipped with a parking brake system.
- The aircraft has two fuel gauges which shows the level in each group of fuel tank.
- Although there are two cockpit doors equipped with window lifters, usually only the right one is used. They can't be opened during flight, but can be jettisoned to bail out.
- The aircraft is equipped with mechanical releasing system for a single bomb.
- The gunsight has a sliding sun-filter. There is also a back-up mechanical sight which can be used if main sight is damaged.
 
Basic data and recommended positions of the aircraft controls:
1. Starting the engine:
- recommended position of the mixture control lever: Auto Rich (auto mixture control)
- recommended position of the radiator/cowl flap control handle: close
- recommended position of the prop pitch control handle: 100%
- recommended position of the throttle lever: 10%
- before taxiing, the parking brake must be released
 
2. Recommended mixture control lever positions for various flight modes: Auto Rich (auto mixture control)
 
3.1 Recommended positions of the radiator/cowl flap control handle for various flight modes:
- takeoff: open 50%
- climb: open 100%
- cruise flight: open 40%
- combat: open 100%
 
3.2 Recommended positions of the radiator/cowl flap control handle for various flight modes:
- takeoff: open 50%
- climb: open 100%
- cruise flight: open 40%
- combat: open 80%
 
4. Approximate fuel consumption at 2000 m altitude:
- Cruise engine mode: 15.2 l/min
- Combat engine mode: 24.1 l/min
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