Pe-2 ser.35 / IL-2 Sturmovik: Great Battles
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Bomber
Pe-2 ser.35
History
Specifications

The Petlyakov bomber was originally conceived as the VI-100 twin-engine high-altitude fighter, but later it was proposed to convert the VI-100 into a front-line dive bomber. On May 1, 1940, the prototype took part in an air parade over Red Square in Moscow. On November 18, 1940, a production aircraft made its first flight, designated Pe-2 in honor of the chief designer.

The dive speed was limited by brake flaps located under the wings: the safety margin allowed the aircraft to maintain a dive angle of up to 70 degrees. The aircraft was equipped with an unprecedented number of electric systems for the domestic aircraft industry: electric motors operated trim tabs, landing and brake flaps, water radiator shutters, and provided control of the stabilizer and the pump that maintained pressure in the landing gear hydraulic system.

Warfare quickly tested the solutions built into the aircraft, and the experience gained in combat greatly accelerated the process of improving the aircraft. Both the engines and the weapons were improved. As early as July 1941, the 35 series began to arrive at the front.

The Pe-2 of the 35th series was a twin-engine cantilever monoplane with a low-mounted wing, a two-finned tail, and a two-strut landing gear with a tail wheel. The monocoque fuselage consisted of the nose section with the forward cockpit, the fuselage center section and the fuselage tail section (with a bomb bay between the fuselage center section and the fuselage tail), the tail section with the gunner's and radio operator's cabins, and a removable tail cone. The pilot's and navigator's cockpits in front and below had large windows to improve forward and downward visibility during dive bombing. The armor protected the pilot, navigator, and tail gunner only against attacks from the rear.

The 35th series was equipped with improved Klimov M-105RA engines with a takeoff power of 1100 hp. They featured a strengthened crankcase and main connecting rod, a floatless carburetor, and a more powerful alternator.

The defensive armament included a fuselage-mounted ShKAS machine gun and a large-caliber machine gun at the lowest point at the gunner-radio operator position, and a dorsal ShKAS machine gun at the navigator’s position, which in the stowed position was closed with a characteristic "turtle" — in the combat position, it slid along guides down and back inside the fuselage, enabling the navigator the ability to fire the gun. The offensive armament included two machine guns, one of which was of large caliber.

The internal bomb armament consisted of six 100 kg bombs (four in the central bomb bay and one in each of the bomb bays in the rear sections of the nacelles). Four more of the same bombs could be mounted on an external rack near the center section. Bombs of 250 and 500 kg were suspended from the outside only. During a dive, only bombs from an external mount could be dropped.

The Pe-2 was the main frontline bomber of the Soviet Air Force from the first to the last day of the war and was effectively used in almost all major operations of the Soviet forces. The Pe-2 was used as a bomber, a reconnaissance aircraft, and a day and night fighter. The Pe-2, affectionately called the "Pawn" by its crew, fought on all fronts and in the naval aviation of all fleets. In the hands of Soviet pilots, the Pe-2 fully revealed its inherent capabilities — speed, maneuverability, powerful weapons, strength, reliability, and survivability were its distinguishing features. Despite the resistance of air defenses and enemy fighters, the bomber's dive attacks destroyed warehouses, bridges, fortified positions, and other targets.

Used sources:

1. V. Shavrov “History of aircraft designs in the USSR 1938-1950.” 1988

2. V. Kotelnikov, A. Medved, D. Khazanov “Pe-2 dive bomber” 2004

3. Materials from the site airwar.ru

Indicated stall speed in flight configuration: 175..200 km/h
Indicated stall speed in takeoff/landing configuration: 148..169 km/h
 
Dive speed limit: 790 km/h
Maximum load factor: 11 G
Stall angle of attack in flight configuration: 13.9 °
Stall angle of attack in landing configuration: 9.8 °
 
Maximum true air speed at sea level, engine mode - Nominal: 434 km/h
Maximum true air speed at 2000 m, engine mode - Nominal: 476 km/h
Maximum true air speed at 5000 m, engine mode - Nominal: 521 km/h
 
Service ceiling: 9100 m
Climb rate at sea level: 9.3 m/s
Climb rate at 3000 m: 8.4 m/s
Climb rate at 6000 m: 5.6 m/s
 
Maximum performance turn at sea level: 30.5 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 39.9 s, at 270 km/h IAS.
 
Flight endurance at 3000 m: 3.7 h, at 300 km/h IAS.
 
Takeoff speed: 160..200 km/h
Glideslope speed: 220..240 km/h
Landing speed: 155..165 km/h
Landing angle: 12.5 °
 
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 Nominal power.
 
Engine:
Model: M-105RA
Maximum power in Nominal mode at sea level: 1020 HP
Maximum power in Nominal mode at 2000 m: 1100 HP
Maximum power in Nominal mode at 4000 m: 1050 HP
 
Engine modes:
Nominal (unlimited time): 2700 RPM, 910 mm Hg
 
Water rated temperature in engine output: 70..85 °C
Water maximum temperature in engine output: 100 °C
Oil rated temperature in engine output: 90..100 °C
Oil maximum temperature in engine output: 110 °C
 
Supercharger gear shift altitude: 2700 m
 
Empty weight: 6078 kg
Minimum weight (no ammo, 10% fuel): 6640 kg
Standard weight: 7697 kg
Maximum takeoff weight: 8712 kg
Fuel load: 1129 kg / 1505 l
Useful load: 2634 kg
 
Forward-firing armament:
12.7mm machine gun "UB", 150 rounds, 1000 rounds per minute, nose-mounted
7.62mm machine gun "ShKAS", 450 rounds, 1800 rounds per minute, nose-mounted
 
Defensive armament:
Top: 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute
Belly: 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute
Side: 7.62mm machine gun "ShKAS", 225 rounds, 1800 rounds per minute
 
Bombs:
Up to 10 x 104 kg general purpose bombs "FAB-100M"
Up to 4 x 254 kg general purpose bombs "FAB-250sv"
Up to 2 x 512 kg general purpose bombs "FAB-500M"
 
Rockets:
10 x 23 kg rockets "ROS-132", HE payload mass 9.1 kg
 
Length: 12.69 m
Wingspan: 17.12 m
Wing surface: 40.8 m²
 
Combat debut: July 1941
 
Operation features:
- The engine has a two-stage mechanical supercharger which must be manually switched at 2700m altitude.
- Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight.
- 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. The governor is electrically actuated and takes a long time to reach the required revolutions, up to 45 seconds when going from minimum to maximum.
- Water and oil radiator shutters are controlled manually.
- The aircraft has trimmers for all flight-controls: pitch, roll and yaw.
- The aircraft has fence-type airbrakes which are located under the wing and are used to slow the descent during steep dive bombing.
- The aircraft is equipped with an automatic dive system. When the dive system is engaged, the plane enters a dive when the airbrakes are extended (passing through the 45 ° position) and will recover from the dive when you either press the bomb drop button or the dive recovery button to exit the dive (LCtrl + D by default). The dive system controls the elevator trim - for correct operation, the trimmer must be in the range between -4.5 ° to +4.5 ° before turning on the dive system. If the trimmer is outside this range, the aircraft has been trimmed manually, or if the airbrakes are retracted while the dive system is engaged, the dive system will be turned off.
- Landing flaps have electro-hydraulic actuator and they can be extended to any angle up to 50°. When landing and the flaps are fully extended the angle of attack for a stall is less than landing pitch angle. For this reason, it is prohibited to extend flaps to more than to 35° (70%) on landing.
- The aircraft has an automatically controlled horizontal stabilizer. An automatic control system adjusts the stabilizer angle depending on the extended angle of the landing flaps.
- The aircraft tailwheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing.
- The aircraft has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- The aircraft has three fuel gauges which shows the level in the fuselage fuel tank, left wing tanks and right wing tanks.
- The canopy has an emergency release system for bailouts.
- The aircraft is equipped with a bomb salvo controller, it has four release modes: drop single, drop two in a salvo, drop four in a salvo or drop all bombs in salvo. There is also a controller for a drop delay between each bomb in the salvo.
- When rockets are installed there is a salvo controller, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. Aircraft has a fire control system that is designed for eight rockets. However, for added punch, ten rockets were typically loaded. In that case, the ninth rocket will fire with the seventh and the tenth will fire with the eighth.
 
Basic data and recommended positions of the aircraft controls:
1. Starting the engine:
- recommended position of the mixture control lever: 100%
- recommended position of the radiator control handle: open 50%
- recommended position of the prop pitch control handle: 100%
- recommended position of the throttle lever: 10%
 
2. Recommended mixture control lever positions for various flight modes:
- When running the engine at low throttle near the ground, the mixture control lever should be in the position of about 50%.
- When the engine is running at full throttle near the ground, the mixture control lever should be in the 75-80% position.
- As you gain altitude, the altitude corrector closes.
 
3.1 Recommended positions of the oil radiator control handle for various flight modes:
- takeoff: open 50%
- climb: open 100%
- cruise flight: open 100% (in winter conditions - open 50%)
- combat: open 50%
 
3.2 Recommended positions of the water radiator control handle for various flight modes:
- takeoff: open 50%
- climb: open 100%
- cruise flight: open 60% (in winter conditions - open 20%)
- combat: open 50%
 
4. Approximate fuel consumption at 2000 m altitude:
- Cruise engine mode: 13.1 l/min
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