P-51B-5 / IL-2 Sturmovik: Great Battles
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Fighter
P-51B-5
History
Specifications

In 1940, the British offered North American Aviation the opportunity to produce the P-40 fighter for Great Britain under license from Curtiss, but North American representatives proved that they could quickly develop and produce a more advanced aircraft of their own design. In late 1940, the prototype of the new NA-73 fighter was built, and in April 1941, the first production aircraft was produced, known in Great Britain as the Mustang I.

The main drawback of the aircraft soon became apparent, related to the low-altitude Allison engine installed on it: having excellent characteristics at low levels, the aircraft lost all its advantages as it climbed higher — so the first aircraft were used as attack and reconnaissance aircraft. But high-altitude fighters were needed, and so it was decided to install a high-altitude British Merlin engine on the Mustang. The Americans, having learned of this work by the British, decided to do the same and purchased a license to produce these engines. The result of the installation of this engine was the P-51B (NA-101), the prototype of which took to the skies on October 30, 1942. The second production modification of this aircraft was the P-51B-5.

The P-51B-5 was a single-seat, single-engine, all-metal, cantilevered monoplane with a low-mounted wing — a feature of the wing was the use of a thin laminar airfoil. Airflow flowed smoothly around the wing without turbulence, so the new profile had much less drag and could therefore give the aircraft more speed with the same engine. The aerodynamically clean fuselage was divided into three parts: forward, center, and tail. The pilot was situated in the cockpit in the middle of the fuselage. The canopy framing was revised — this improved the aerodynamics of the aircraft but worsened the visibility to the rear. Protection for the pilot included armored glass in the front and an armored seat back with a headrest. When designing the engine, many design elements were strengthened, and the location of the air intake and the design of the cooling system were changed.

The P-51B-5 was equipped with a Packard V-1650-3 engine of 1620 hp, which was a licensed version of the Rolls-Royce Merlin engine. It is worth noting that it was possible to establish engine production in the USA only by replacing some of the workers and engineering and technical personnel with British personnel.

The armament of the modification consisted of 4 heavy machine guns in the wings. The disadvantage of this weapon system was that the ammunition belt feed sleeves tended to bend because the machine guns were mounted at a slight angle, which sometimes caused them to jam.

Thanks to the reinforced wing structure, the aircraft could carry two bombs up to 1,000 pounds (454 kg) under the wing, or drop tanks or unguided rockets.

To increase the range of the aircraft, an additional fuel tank was installed behind the pilot's seat. Initially, such a tank was not installed on the production aircraft, but after approximately the production of the first 250 aircraft, the tank began to be installed at the Inglewood plant, and those aircraft that had not made it to the front and did not yet have a tank were sent to workshops, where they received all the latest modifications, including the tank, which was also installed in case of repairs after damage received in battle. Sometimes the modified aircraft were designated B-7, but most often the aircraft with an additional tank had a white or black cross painted on the left side, depending on the color of the base paint.

The first production P-51Bs arrived in Europe in September 1943, and the pilots of the American 354th Fighter Group flew their first combat mission in the P-51B on December 1st.

After landing on the continent, the Mustangs were sometimes used for attack missions but were still primarily used as escort fighters. In general, the formation of American bombers called the "combat box" provided a serious defense, hitting the enemy with heavy machine gun fire from all directions. The tight formation made it possible to concentrate the fire of several planes on one enemy fighter, so for the Germans, the primary task was to destroy the "box." Then everything was easier: several Messerschmitts or Focke-Wulfs attacked the bomber from different sides and often succeeded. Thus, the losses of the bombers were significantly reduced in the presence of an escort that repelled the attacks of the German fighters.

1. “American Warplanes of World War II” by David Donald, 1995
2. S. Ivanov “P-51 Mustang”, “War in the Air” No. 124 2005
3. Materials from the site airwar.ru

Indicated stall speed in flight configuration: 158..192 km/h (98..119 mph)
Indicated stall speed in takeoff/landing configuration: 147..177 km/h (91..110 mph)
 
Dive speed limit: 812 km/h (505 mph)
Maximum load factor: 10.0 G
Stall angle of attack in flight configuration: 19.0 °
Stall angle of attack in landing configuration: 16.0 °
 
Packard V-1650-3:
 
Maximum true air speed at sea level, engine mode - WEP: 600 km/h (373 mph)
Maximum true air speed at 9000 m (29530 feet), engine mode - WEP: 700 km/h (435 mph)
 
Maximum true air speed at sea level, engine mode - WEP, with 150 grade fuel: 619 km/h (385 mph)
Maximum true air speed at 7750 m (25430 feet), engine mode - WEP, with 150 grade fuel: 713 km/h (443 mph)
 
Maximum true air speed at sea level, engine mode - Combat: 582 km/h (362 mph)
Maximum true air speed at 9500 m (31170 feet), engine mode - Combat: 691 km/h (429 mph)
 
Maximum true air speed at sea level, engine mode - Cruise: 506 km/h (314 mph)
Maximum true air speed at 10000 m (32810 feet), engine mode - Cruise: 662 km/h (411 mph)
 
Service ceiling: 12680 m (41600 feet)
 
Climb at engine mode - WEP
Climb rate at sea level: 18.6 m/s (3661 feet/min)
Climb rate at 3000 m (9843 feet): 17.8 m/s (3504 feet/min)
Climb rate at 6000 m (19685 feet): 13.1 m/s (2579 feet/min)
 
Maximum performance turn at sea level: 19.2 s, at 290 km/h (180 mph) IAS.
Maximum performance turn at 3000 m (9843 feet): 28.0 s, at 295 km/h (183 mph) IAS.
 
Flight endurance at 3000 m (9843 feet): 4.3 h, at 350 km/h (217 mph) IAS.
 
Packard V-1650-7:
 
Maximum true air speed at sea level, engine mode - WEP: 604 km/h (375 mph)
Maximum true air speed at 7500 m (24600 feet), engine mode - WEP: 717 km/h (446 mph)
 
Maximum true air speed at sea level, engine mode - WEP, with 150 grade fuel: 626 km/h (389 mph)
Maximum true air speed at 6250 m (20505 feet), engine mode - WEP, with 150 grade fuel: 721 km/h (448 mph)
 
Maximum true air speed at sea level, engine mode - Combat: 588 km/h (365 mph)
Maximum true air speed at 8500 m (27890 feet), engine mode - Combat: 713 km/h (443 mph)
 
Maximum true air speed at sea level, engine mode - Cruise: 521 km/h (324 mph)
Maximum true air speed at 8500 m (27890 feet), engine mode - Cruise: 665 km/h (413 mph)
 
Service ceiling: 12680 m (41600 feet)
 
Climb at engine mode - WEP
Climb rate at sea level: 19.3 m/s (3799 feet/min)
Climb rate at 3000 m (9843 feet): 18.0 m/s (3543 feet/min)
Climb rate at 6000 m (19685 feet): 11.8 m/s (2323 feet/min)
 
Maximum performance turn at sea level: 19.0 s, at 290 km/h (180 mph) IAS.
Maximum performance turn at 3000 m (9843 feet): 28.0 s, at 295 km/h (183 mph) IAS.
 
Flight endurance at 3000 m (9843 feet): 4.3 h, at 350 km/h (217 mph) IAS.
 
Takeoff speed: 185..200 km/h (115..125 mph)
Glideslope speed: 185..210 km/h (115..130 mph)
Landing speed: 175..195 km/h (110..120 mph)
Landing angle: 12.9 °
 
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 68% of fuel.
Note 4: turn times are given for WEP power.
 
Engine:
Model: Packard V-1650-3
Maximum power in WEP mode at sea level: 1550 HP
Maximum power in Combat mode at sea level: 1385 HP
 
Maximum power in WEP mode at 7860 m (25800 feet): 1235 HP
Maximum power in Combat mode at 7100 m (23300 feet): 1360 HP
 
Engine:
Model: Packard V-1650-7
Maximum power in WEP mode at sea level: 1650 HP
Maximum power in Combat mode at sea level: 1490 HP
 
Maximum power in WEP mode at 5800 m (19030 feet): 1525 HP
Maximum power in Combat mode at 6500 m (21325 feet): 1390 HP
 
Engine modes:
Cruise (unlimited time): 2700 RPM, 46 inch Hg
Combat power (up to 15 minutes): 3000 RPM, 61 inch Hg
WEP (up to 5 minutes): 3000 RPM, 67 inch Hg
WEP with 150 grade fuel (up to 5 minutes): 3000 RPM, 75 inch Hg
 
Water rated temperature in engine output: 100..110 °C
Water maximum temperature in engine output: 121 °C
Oil rated temperature in engine intake: 80 °C
Oil maximum temperature in engine intake: 90 °C
 
Supercharger gear shift altitude: automatic with possibility of manual switch to low gear
 
Empty weight: 3340 kg (7363 lb)
Minimum weight (no ammo, 10% fuel): 3560 kg (7849 lb)
Standard weight: 4389 kg (9676 lb)
Maximum takeoff weight: 5667 kg (12493 lb)
Fuel load: 732 kg (1614 lb) / 1020 l (269 gal)
Useful load: 2234 kg (4925 lb)
 
Forward-firing armament:
4 x 12.7mm machine gun "M2 .50", 350 rounds for inboard and 280 rounds for outboard, 850 rounds per minute, wing-mounted
 
Bombs:
Up to two 500 lb general purpose bomb "M64"
Up to two 1000 lb general purpose bomb "M65" or "MC 1000"
 
Rockets:
6 x unguided rockets "M8" in two "M10" launchers that can be jettisoned
 
Length: 9.84 m (32 3-5/16 feet)
Wingspan: 11.29 m (37 5/16 feet)
Wing surface: 22.30 m² (240 feet²)
 
Combat debut: winter 1943-1944
 
Operation features:
- COMBAT, AEROBATIC MANEUVERS AND INSTRUMENT FLYING ARE FORBIDDEN AT FULL FUEL RESERVE! The aircraft is unstable with full rear fuel tank. This limit is lifted when there is no more than 20 gallons (around 75% fuel left) in the rear tank. This tank is completely empty at 68% total fuel level.
- It is possible to reach dangerously high Mach numbers in a dive: the aircraft starts to shake and the loss of control is possible. Reduce the throttle and gently return to a horizontal flight.
- The engine has a emergency boost mode. To set boost mode it is necessary to pull the boost knob and set full throttle.
- The engine is equipped with the automatic governor of the manifold pressure that works when the throttle is set to 1/3 position or above.
- The engine has a two stage mechanical supercharger which does not require manual control. It can be switched to the low gear manually.
- The engine is equipped with an automatic fuel mixture control which maintains optimal mixture if the mixture lever is set to AUTO RICH (100%) position. To stop the engine mixture lever should be set to the Cut Off (0%) position.
- Engine RPM has an automatic governor that controls the propeller pitch to maintain the required RPM.
- The water and oil radiators shutters are operated automatically, but there is a manual mode.
- The aircraft has trimmers for all flight-controls: pitch, roll and yaw.
- Landing flaps have a hydraulic actuator and can be extended to 10°, 20°, 30°, 40° or 50°.
- Each tank has a dedicated fuel level indicator: wing tank inidicators are located on the cockpit floor and the rear tank indicator is behind the pilot seat on the left.
- The tailwheel rotates freely, but moving the control stick back locks it so it rotates by the pedals input.
- 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 signal lamp lights up when the landing gear is up and the throttle is in the backward position or when the landing gear is down, but the throttle is in the forward position.
- The aircraft is equipped with formation lights.
- 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 gyroscopic gunsight automatically calculates required angular deflection while firing at a target. It has 3 modes: fixed reticle, fixed and gyro reticle, gyro reticle. The angular deflection will be calculated correctly only if the target range is set properly. To set the range, adjust the target base first using separate controls and then set the range by adjusting the size of the range-finding reticle to be the same as the target size.
 
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 control handle: auto radiators control
- 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 mixture control
 
3. Recommended positions of the radiators control handle for various flight modes: auto radiators control
 
4. Approximate fuel consumption at 2000 m altitude:
- Cruise engine mode: 6.3 l/min
- Combat engine mode: 13.4 l/min
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