P-38J-25 / IL-2 Sturmovik: Great Battles
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Fighter
P-38J-25
History
Specifications

In 1937, the U.S. Army Air Corps announced a competition for a twin-engine high-altitude fighter-interceptor, which was won by Lockheed with a very original design of a twin-boom aircraft. The prototype took to the skies on January 27, 1939, and in 1941 the first P-38D fighters entered service (at that time in the United States, the first combat-ready aircraft models were immediately assigned the index D), which in England received the name "Lightning." The plane has become an icon in many ways:

  • It was Lockheed's first production fighter;

  • The first twin-engine interceptor to enter U.S. service;

  • The world's first fighter with a nose landing gear;

  • The first in the U.S. to use countersunk rivets to join the skin;

  • It was the first to have a teardrop-shaped all-around canopy;

  • It was the first American fighter to shoot down a German plane in World War II;

  • The first American fighter to reach Berlin;

  • The first Allied aircraft to land on Japanese territory after the surrender.

Being the first in many ways, the aircraft could not help but have shortcomings, but as combat and operational experience accumulated, all were eliminated and in mid-1943 the P-38J modification went into production. It was produced in several modifications, the most advanced of which was the P-38J-25.

The P-38J-25 Lightning was a single-seat, twin-engine, all-metal monoplane with a three-post landing gear. The wing consisted of a center section and two removable sections. The central section carried self-sealing fuel tanks and a central nacelle. In the front part of the nacelle, there was a weapons compartment and a recess for the front landing gear, and in the rear, there was a pilot's cockpit with a drop-shaped transparent canopy. The cockpit armor consisted of a set of armor plates that covered the pilot in front and behind. The tail booms were composed of three compartments. The front compartment of each of them was made integral with the middle section and served to install the engine. A turbocharged compressor unit was located in the upper rear part of the compartment. Radiators for the engine cooling system were mounted in the center sections of the tail booms. The design of the cooling system was changed on the P-38J and new air intakes for the cooling radiators were installed with a more advanced aerodynamic shape. The rear compartments were used to mount the tail. Starting with the P-38J-15, the place of the intercoolers in front of the wing consoles was taken by additional fuel tanks with a total capacity of 416 liters, but they were not installed on all P-38Js: aircraft with additional tanks were marked with a red cross on the fuselage next to the manufacturer's plate.

Earlier models suffered from loss of control during high-speed dives, so the P-38J was equipped with special flaps that allowed it to recover quickly and safely from a dive. Aileron boosters made the P-38J-25 one of the most maneuverable fighters in the world.

The propulsion system consisted of two liquid-cooled Allison V-1710-89/91 engines, each developing 1425 hp up to an altitude of 7200 m. To compensate for the torque of the two engines, their shafts rotated in different directions, hence the different designations for the left and right modifications.

The small arms consisted of a 20 mm cannon and four heavy machine guns. The location of all weapons in the nose of the aircraft, without the need to synchronize with the propeller, made it possible to achieve high salvo power and shooting accuracy. Bombs or drop tanks could be carried under the center section.

P-38 fighters were widely used by the U.S. Army Air Forces during World War II, especially in the Pacific theater. It is worth noting that it was the P-38 Lightning that was flown by the two most successful fighter pilots in the history of American military aviation — Thomas McGuire (38 victories) and Richard Ira Bong (40 victories). The P-38 was also used for a variety of other missions, including dive and level bombing, night missions, and photographic reconnaissance. In Europe, the Lightning was less popular and was used primarily for attack missions.

Interestingly, this was the only fighter produced from the attack on Pearl Harbor to the end of the war. A total of 2,970 P-38Js were built.

Used sources:

1. Francillon “Lockheed aircraft since 1913” -1987

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

3. S. Ivanov “R-38 Lightning Photo Archive” War in the Air No. 103 2004

4. Materials from the site airwar.ru

Indicated stall speed in flight configuration: 179..220 km/h (111..137 mph)
Indicated stall speed in takeoff/landing configuration: 149..185 km/h (93..115 mph)
 
Dive speed limit: 725 km/h (450 mph)
Maximum load factor: 9.0 G
Stall angle of attack in flight configuration: 14.1 °
Stall angle of attack in landing configuration: 11.5 °
 
Maximum true air speed at sea level, engine mode - WEP: 557 km/h (346 mph)
Maximum true air speed at 7860 m (25800 feet), engine mode - WEP: 674 km/h (419 mph)
 
Maximum true air speed at sea level, engine mode - Combat: 540 km/h (336 mph)
Maximum true air speed at 8500 m (27890 feet), engine mode - Combat: 670 km/h (416 mph)
 
Service ceiling: 12350 m (40500 feet)
 
Climb at engine mode - WEP
Climb rate at sea level: 20.4 m/s (4020 feet/min)
Climb rate at 3000 m (9843 feet): 19.1 m/s (3758 feet/min)
Climb rate at 6000 m (19685 feet): 15.0 m/s (2953 feet/min)
 
Climb at engine mode - Combat
Climb rate at sea level: 12.8 m/s (2518 feet/min)
Climb rate at 3000 m (9843 feet): 11.5 m/s (2258 feet/min)
Climb rate at 6000 m (19685 feet): 9.4 m/s (1844 feet/min)
 
Maximum performance turn at sea level: 20.0 s, at 310 km/h (195 mph) IAS.
Maximum performance turn at 3000 m (9843 feet): 28.3 s, at 320 km/h (200 mph) IAS.
 
Flight endurance at 3000 m (9843 feet): 5.8 h, at 350 km/h (217 mph) IAS.
 
Takeoff speed: 160..175 km/h (100..110 mph)
Glideslope speed: 185..210 km/h (115..130 mph)
Landing speed: 150..175 km/h (95..110 mph)
Landing angle: 7.0 °
 
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 and 70% of fuel.
Note 4: turn times are given for WEP power.
 
Engine:
Model: Allison V-1710-89 (left) and V-1710-91 (right)
Maximum power in WEP mode at sea level: 1550 HP
Maximum power in WEP mode at 7860 m (25800 feet): 1505 HP
 
Engine modes:
Cruise (unlimited time): 2600 RPM, 44 inch Hg
Combat power (up to 15 minutes): 3000 RPM, 54 inch Hg
WEP (up to 5 minutes): 3000 RPM, 60 inch Hg
 
Maximum continuous turbocharger RPM: 24000
Maximum turbocharger RPM for up to 15 minutes: 26400
 
Water rated temperature in engine output: 85 °C
Water maximum temperature in engine output: 105 °C
Oil rated temperature in engine output: 105 °C
Oil maximum temperature in engine output: 115 °C
 
Supercharger gear shift altitude: single gear
 
Empty weight: 6356 kg (14013 lb)
Minimum weight (no ammo, 10% fuel): 6662 kg (14687 lb)
Standard weight: 7890 kg (17395 lb)
Maximum takeoff weight: 10113 kg (22295 lb)
Fuel load: 1132 kg (2496 lb) / 1575 l (416 gal)
Useful load: 3757 kg (8282 lb)
 
Forward-firing armament:
20mm gun "M2", 150 rounds, 650 rounds per minute, nose-mounted
4 x 12.7mm machine gun "M2.50", 300 rounds, 850 rounds per minute, nose-mounted
It is possible to increase the ammo load to 500 rounds per gun.
 
Bombs:
Up to six 500 lb general purpose bomb "M64"
Up to four 1000 lb general purpose bomb "M65"
Up to two 2000 lb general purpose bomb "M66"
 
Rockets:
6 x unguided rockets "M8" in two "M10" launchers that can be jettisoned
 
Length: 10.89 m (35.73 feet)
Wingspan: 15.85 m (52 feet)
Wing surface: 30.4 m² (327 feet²)
 
Combat debut: 1944
 
Operation features:
- In addition to the automatic single-stage supercharger, each engine is equipped with the automatic turbo-supercharger.
- The turbo-supercharger is powered by the engine exhaust backpressure and is regulated automatically by the pilot throttle control in the cockpit using the shutters on the exhaust pipes.
- It should be noted that turbocharger RPM changes relatively slowly and not immediately after a control lever adjustment. For instance, during takeoff it's necessary to keep the brakes pressed for several seconds after moving the throttle to takeoff position and begin the run only when the turbocharger RPM increases sufficiently to reach 54 inches of pressure.
- The automatic fuel mixture control maintains optimal mixture if mixture lever is set to Auto Rich (70%) position. To use automatic mixture leaning to reduce the fuel consumption during flight set the mixture lever to Auto Lean (30%) position. In a case of malfunction of the automatic mixture control, the mixture lever should be set to Full Rich (move the lever completely forward) position. To stop the engine, set it to the Idle Cut Off (0%) position.
- The automatic engine governor keeps the set engine RPM by adjusting the propeller pitch using an electric actuator (it is possible to turn it off and control the propeller pitch manually). The propellers can be feathered.
- To check a low fuel level warning lamps, press and hold the corresponding button (RShift+I by default).
- The aircraft has pitch and yaw flight-control trimmers.
- Landing flaps have a hydraulic actuator and can be extended to any angle up to 40°. There is also a fixed "maneuver" flaps position that can be set by a short flaps button press ("F" by default).
- The aircraft is equipped with hydraulic aileron actuators, making their operation and good roll performance at high speeds possible. The actuators are turned on using a special valve on the left side of the cockpit and require at least 1200 psi pressure in the hydraulic system, so they should be turned off if there is only one engine running. In the sim, they are turned on and off automatically.
- 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 landing gear indicator lamp lights up if the landing gear is neither extended nor retracted. The extension of the nose wheel can also be checked by its reflection in the mirrors on the inner sides of the engine nacelles and by the pressure drop in the hydraulic system during the landing gear operation.
- There are signal lamps warning about the low fuel level in the outer wing tanks (the primary fuel source) and separate fuel indicators for the left and right fuel tank pairs.
- The canopy has an emergency release system for bailouts.
- The windows on the sides of the canopy can be lowered during flight, but this can cause the excessive shaking of the plane.
- The electric bomb controller allows dropping the bombs one by one from the left and right racks or by pairs.
- The unguided rockets are launched using the electric controller which allows single, pair, triple and salvo (all rockets at 0.1 seconds interval) launch. The rocket containers are jettisonable.
 
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 oil radiator / cowl flaps flap control handle: auto radiator control
- recommended position of the prop pitch control handle: 0%
- recommended position of the throttle lever: 20%
- before taxiing, the parking brake must be released
 
2. Recommended mixture control lever positions for various flight modes: Auto Rich (auto mixture control)
 
3. Recommended positions of the oil radiator / cowl flaps flap control handle for various flight modes: auto control of oil radiators / cowl flaps
 
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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