Yak-7B series 36 / IL-2 Sturmovik: Great Battles
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Fighter
Yak-7B series 36
History
Specifications

The design bureau of the Deputy People's Commissar for the Aircraft Industry Yakovlev was among those involved in creating a new generation of combat aircraft in the USSR, working on the I-26 project. The specialization of the design bureau, which had previously created sport aircraft, had a positive impact on the project. The fighter was to have high speed and maneuverability thanks to efficient aerodynamic design and a rational layout with all large masses near the center of gravity.

The prototype flew for the first time on January 13, 1940 and turned out to be "crude": the tests were accompanied by continuous failures, accidents, and even disasters. If Yakovlev had not been a deputy people's commissar, the story of this fighter would probably have ended at the factory testing stage, but due to the use of administrative resources, the aircraft, which was given the name Yak-1, not only entered state tests, but in 1940 was put into mass production even before they were carried out. As a result, it had several major defects, which, however, did not change its overall high rating. During production, the design was continually modified to reflect combat experience.

In March 1941 a two-seater training version of the Yak-7 was produced to train pilots for Yak aircraft, but the lack of fighters at the front naturally led to the idea of converting the training version into a single-seater combat version: this was the Yak-7, and later its modifications Yak-7, 7A, and Yak-7B.

The Yak-7B was a single-seat front-line fighter monoplane with a low wing of wooden construction and a retractable two-strut landing gear with a tail wheel that was also retractable. Some equipment was removed from the aircraft to lighten the structure, and internal sealing of the fuselage compartments was introduced. The fuselage was mounted on a welded metal frame that was integral with the engine mount.

The water-cooled M-105PF engine was equipped with improved intake ducts to better utilize the manifold pressure and increase the altitude limits. It developed 1240 shp at takeoff and 1200 shp at an altitude of 4000 m.

Armament included a 20 mm cannon mounted in the engine cylinder block and firing through the hollow shaft and propeller transmission, and two UBS heavy machine guns. Racks for two bombs of 50 or 100 kg could be fitted under the wings.

A total of 5,120 Yak-7Bs fitted with the M-105PF engine were produced: they took part in combat for the first time in August 1942 near Stalingrad. The pilots, evaluating the combat qualities of the Yak-7B based on their experience, noted that in terms of flight-tactical data and armament, it was the best fighter of the Air Force at the beginning of 1943. At the same time, its disadvantages were also noted: it was heavy, which made it difficult to gain speed quickly; it had high drag due to the water and oil radiators; and it had no rear view due to the high-back fuselage and space for a second cockpit. They also noted the low power of even the forced induction engine.

Pilots and technicians continued to love this aircraft for its lightness and ease of operation, as well as ease of maintenance, characteristic of the Yakovlev family of fighters. The presence of free space instead of the second cockpit made it possible to transport equipment during relocation.

Used sources:

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

M. Nikolsky “Yak-fighter” Aviation and Cosmonautics magazine No. 5-5 1999

Materials from the site airwar.ru

Indicated stall speed in flight configuration: 155..172 km/h
Indicated stall speed in takeoff/landing configuration: 139..154 km/h
Dive speed limit: 740 km/h
Maximum load factor: 11.5 G
Stall angle of attack in flight configuration: 18°
Stall angle of attack in landing configuration: 16°
 
Maximum true air speed at sea level, engine mode - Nominal, 2700 RPM: 526 km/h
Maximum true air speed at 2000 m, engine mode - Nominal, 2700 RPM: 565 km/h
Maximum true air speed at 4000 m, engine mode - Nominal, 2700 RPM: 586 km/h
 
Service ceiling: 10660 m
Climb rate at sea level: 16.9 m/s
Climb rate at 3000 m: 14.3 m/s
Climb rate at 6000 m: 8.6 m/s
 
Maximum performance turn at sea level: 19..20 s, at 310 km/h IAS.
Maximum performance turn at 3000 m: 24..25 s, at 310 km/h IAS.
 
Flight endurance at 3000 m: 1.9 h, at 350 km/h IAS.
 
Takeoff speed: 170..175 km/h
Glideslope speed: 200 km/h
Landing speed: 145..165 km/h
Landing angle: 11.5°
 
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 (2700 RPM) power.
 
Engine:
Model: M-105PF
Maximum power in Nominal mode (2700 RPM) at sea level: 1210 HP
Maximum power in Nominal mode (2700 RPM) at 700 m: 1260 HP
Maximum power in Nominal mode (2700 RPM) at 2700 m: 1180 HP
 
Engine modes:
Nominal (unlimited time): 2600/2700 RPM, 1050 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: 115 °C
 
Supercharger gear shift altitude: 2000 m
 
Empty weight: 2302 kg
Minimum weight (no ammo, 10% fuel): 2630 kg
Standard weight: 3002 kg
Maximum takeoff weight: 3229 kg
Fuel load: 305 kg / 420 l
Useful load: 927 kg
 
Forward-firing armament:
20mm gun "SsVAK", 120 rounds, 800 rounds per minute, nose-mounted
2 x 12.7 mm machine gun "UBS", 400 rounds, 900 rounds per minute, synchronized
 
Bombs:
2 x 50 kg general purpose bombs "FAB-50sv"
2 x 104 kg general purpose bombs "FAB-100M"
 
Length: 8.5 m
Wingspan: 10 m
Wing surface: 17.15 m²
 
Combat debut: early 1943
 
Operation features:
- The engine has a two-stage mechanical supercharger which must be manually switched at 2000 m 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.
- Water and oil radiator shutters are controlled manually.
- The aircraft has only the pitch flight-control trimmer.
- Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 250 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing.
- The aircraft has a manual control for the tailwheel lock. The unlocked tailwheel has a 90° turn limit. The tailwheel should be locked when taxiing straight for a long distance and before 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.
- Fuel gauges are installed on left and right wing fuel tanks, outside of the cockpit. They show remaining fuel level only when there is less than 130 liters of fuel left in the tank.
- It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it.
- The control system for the wing-mounted bomb racks only allows releasing of both bombs together.
 
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 radiators control handles: close
- recommended position of the prop pitch control handle: 100%
- recommended position of the throttle lever: 5%
- before taxiing, you must unlock the tailwheel
 
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. At 8-9 km altitude, the altitude corrector closes to 0%.
 
3.1 Recommended positions of the oil radiator control handle for various flight modes:
- takeoff: open 100%
- climb: open 100%
- cruise flight: open 30%
- combat: open 100%
 
3.2 Recommended positions of the water radiator control handle for various flight modes:
- takeoff: open 100%
- climb: open 100%
- cruise flight: open 50%
- combat: open 80%
 
4. Approximate fuel consumption at 2000 m altitude:
- Cruise engine mode: 7.8 l/min
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