Me 262 A / IL-2 Sturmovik: Great Battles
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Fighter
Me 262 A
History
Specifications

Development of this interceptor began in 1938 under the designation P1065. In 1942, the first operational Jumo-004A engine became available, and the prototype Me 262 V3 with these engines took flight on July 18, 1942. The first production version of the Me 262 A-1a, known by the unofficial nickname "Swallow," was delivered to the test team in July 1944. It was believed at the time that Hitler's demand that the aircraft be changed from an interceptor to a fast fighter-bomber had adversely affected the pace of production.

The Me 262 A was a single-seat all-metal monoplane with 2 turbojet engines. The fuselage was triangular in cross-section, with the width of the base of the triangle being much greater than the height. This shape was chosen because of the need to accommodate four fuel tanks and main gear wheel storage bays. In combination with a low wing, the problem of reducing the harmful interference between the arrow-shaped wing and the fuselage was solved at the same time. The choice of such a wing was explained not by the desire to improve speed characteristics, but by the need to provide the required margin of longitudinal stability of the fighter. The engine type Jumo-004B-1 (later B-2 and B-3) was equipped with a small two-stroke Riedel starter. A 17-liter gasoline reserve was used as fuel for the starter. Apart from this reserve, all other fuel was stored in the fuselage.

The standard armament of the Me 262 A-1a included four 30 mm MK 108 cannons. These weapons were found to have poor ballistics and low reliability. In addition, the following armament variants were available and tested:
  • A-1a/U1: 3 were built. Armament: two 20 mm MG 151/20 cannons (146 rounds each) and two 30 mm MK-103 cannons (72 rounds each);
  • A-1a (Me 262V BK-5): prototype, with one 50 mm MK-214A cannon;
  • A-1b: with rails for twenty-four 55 mm R4M unguided rockets. It is said that fighters of this variant shot down 45 bombers and 15 enemy fighters;
  • A-2a "Sturmvogel": fighter-bomber variant. In addition to the standard armament, it carried one 500 kg or two 250 kg bombs, which were dropped from a dive at an altitude of up to 1000 meters;
  • A-2a/U1: fighter-bomber variant. Two cannons removed, TSA low-level bombing sight installed. 2 built;
  • A-2a/U2: 1 prototype fighter-bomber without cannon armament, with a second crew member and Lotfe 7 gyrostabilized sight installed;
  • A-5a: reconnaissance plane, two 30 mm cannons, and two cameras. One 600-liter or two 300-liter drop tanks could be attached to the bomb racks. A small series was produced, the aircraft was designated Me 262 A-1a/U3.

Anglo-American aviation was a complete success against the Me 262. The reason for this was the suddenness of their appearance since the speed of jet aircraft was much higher than that of piston aircraft. Initially, jet fighters attacked bomber formations in small groups of two or three planes: after shooting down several planes, they broke up the formation and left the fight at high speed. However, the Allies were able to defend themselves with concentrated machine-gun fire and a new tactic of sharp maneuvering at a loss of speed, which the Me 262 pilots could not afford. According to some reports, 150 enemy planes were shot down with the loss of 100 Me 262 As for various reasons.

Fighter-bombers were used to bomb troops and airfields on the Western Front. Allied fighters and anti-aircraft guns offered little resistance to the jet bombers. Me 262 pilots usually flew solo, approaching targets at 8,000 meters during the day, dropping bombs from a shallow dive, and returning home at high speed, beyond the reach of piston-engine fighters.

Pilots found that the Me 262 A-1 was much easier to control than the Luftwaffe's main fighter of the time, the Bf 109 G. Acceleration characteristics were significantly worse than those of propeller-driven aircraft, but the Me 262 had a very high dive speed. The Jumo 004B engines caused many problems: the engine control lever had to be moved very smoothly, otherwise, there was a high probability of the engine catching fire or stalling.

Sources used:

1. W. Creen "The Warplanes of the Third Reich", Galahad Books, 1986

2. "Wings of the Luftwaffe" Translation of W. Creen's book "Combat Airplanes of the Third Reich" by A. Firsov, 1993.

3. "Materials from the site airwar.ru

Indicated stall speed in flight configuration: 165..200 km/h
Indicated stall speed in takeoff/landing configuration: 139..154 km/h
Dive true air speed limit: 1000 km/h
Maximum load factor: 12.5 G
Stall angle of attack in flight configuration: 17°
Stall angle of attack in flight configuration (with slats extended): 23°
Stall angle of attack in landing configuration: 22°
 
Maximum true air speed at sea level, engine mode - Nominal, 8400 RPM: 759 km/h
Maximum true air speed at 6000 m, engine mode - Nominal, 8400 RPM: 780 km/h
Maximum true air speed at 9000 m, engine mode - Nominal, 8400 RPM: 739 km/h
 
Maximum true air speed at sea level, engine mode - Maximal, 8700 RPM: 837 km/h
Maximum true air speed at 6000 m, engine mode - Maximal, 8700 RPM: 871 km/h
Maximum true air speed at 9000 m, engine mode - Maximal, 8700 RPM: 838 km/h
 
Service ceiling: 12000 m
Climb rate at sea level: 19.3 m/s
Climb rate at 6000 m: 9.7 m/s
Climb rate at 9000 m: 5.4 m/s
 
Maximum performance turn at sea level: 32..35 s, at 450 km/h IAS.
Maximum performance turn at 6000 m: 43..48 s, at 380 km/h IAS.
 
Flight endurance at 6000 m: 2 h 20 m, at 475 km/h IAS.
 
Takeoff speed: 200..220 km/h
Glideslope speed: 250 km/h
Landing speed: 165..185 km/h
Landing angle: 12.3°
 
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 Maximal (8700 RPM) power.
 
Engine: 2 x turbo jet
Model: Jumo-004 B1
Maximum power in Maximal mode (8700 RPM) at sea level: 810 kg(f)
Maximum power in Maximal mode (8700 RPM) at 6000 m: 530 kg(f)
Maximum power in Maximal mode (8700 RPM) at 9000 m: 385 kg(f)
 
Engine modes:
Nominal (unlimited time): 8400 RPM
Maximal (15 minutes): 8700 RPM
 
Nominal exhaust temperature: 600 °C
Maximum exhaust temperature: 650 °C
 
Exhaust pressure: 0.2-0.38 kg/cm²
 
Fuel injection pressure: 40-80 kg/cm²
 
Oil rated pressure in engine output: 2 kg/cm²
Oil maximum pressure in engine output: 5 kg/cm²
 
Empty weight: 4146 kg
Minimum weight (no ammo, 10% fuel): 4737 kg
Standard weight: 6400 kg
Weight with full tanks: 6900 kg
Maximum takeoff weight: 7100 kg
Fuel load: 2161 kg / 2570 l
Useful load: 700 kg
 
Forward-firing armament:
2 x 30mm gun "MK 108", 100 rounds, 650 rounds per minute, nose-mounted inner (upper)
2 x 30mm gun "MK 108", 80 rounds, 650 rounds per minute, nose-mounted outer (lower)
 
Bombs:
2 x 249 kg general purpose bombs "SC 250"
500 kg general purpose bombs "SC 500"
 
Length: 10.6 m
Wingspan: 12.6 m
Wing surface: 20.4 m²
 
Combat debut: Summer 1944
 
Operation features:
- The aircraft is equipped with two turbojet engines Jumo-004 B1. They are controlled automatically by the throttle which sets the turbine rotor RPM.
- The engine is equipped with automatic fuel regulator that engaged only at more than 6000 RPM. Therefore, the fuel regulation at lower RPM wasn\'t effective and a careless throttle increase could cause excessive fuel intake, resulting in overheating and possible engine fire.
- At high altitudes it is possible to lean the mixture too much by a sharp throttle decrease, causing a flameout and engine stop. The turbine shouldn\'t be set below 6000-8000 RPM depending on the altitude.
- It is impossible to restart the engine at high altitudes (more than 4000 m).
- The aircraft is equipped with horizontal stabilizer and rudder trim to reduce the load on controls.
- The aircraft is susceptible to Mach tuck when diving at 0.84 M or higher speed. 
- Landing flaps have a hydraulic actuator and they can be extended to any angle up to 55°. The hydraulic valve controlling the flaps can\'t be turned during the landing gear operation (lowering or retracting).
- Landing gear brakes are hydraulic as well and are engaged by pushing a corresponding pedal. The nose gear orients by itself (up to 50° in either direction), has a rotation dampener and dedicated brake handle. The aircraft tends to rotate during a breakaway unless the nose wheel is set forward.
- There are two main (900 l each) and two secondary fuel tanks (600 and 170 l). The fuel transfer from secondary to main tanks using the electric fuel pump is initiated by the pilot when the fuel level in main tanks drops lower than 600 l. The main tanks have fuel level indicators and emergency fuel lamps (they light up when there are less than 250 l left).
 
Basic data and recommended positions of the aircraft controls:
1. Starting the engine:
- recommended position of the mixture control lever: auto mixture control
- recommended position of the throttle lever: 0%
 
2. Recommended mixture control lever positions for various flight modes: auto mixture control
 
3. Recommended positions of the radiator/cowl flap control handle for various flight modes:  no radiators/cowl flaps
 
4. Approximate fuel consumption at 2000 m altitude:
- Cruise engine mode: 18.8 l/min
- Combat engine mode: 28.3 l/min
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