Yak-1 ser.69 / IL-2 Sturmovik: Great Battles
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Fighter
Yak-1 ser.69
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 constantly changed, sometimes quite fundamentally: for example, the wing design was completely changed and the oil system was redesigned several times.

The Yak-1 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 support. The fuselage was mounted on a welded metal frame that was integral with the engine mount. To give the fuselage a streamlined shape, bulkheads were installed at the top and bottom of the frame: the upper one, which was a continuation of the cockpit canopy, was lined with bakelite plywood and had 2 windows to improve rearward visibility.

The water-cooled M-105PF engine developed 1240 hp at takeoff and 1200 hp at an altitude of 4000 m and drove a VISH-61P three-bladed propeller.

The armament consisted of a 20 mm cannon mounted in the camber of the engine cylinder block and firing through the hollow shaft and propeller transmission, and two synchronized rifle-caliber machine guns above the engine. Racks for two 50 kg or 100 kg bombs or launch rails for six unguided rockets could be fitted to the underside of the wings.

The Yak-1 of the 69th series appeared at the front in the summer of 1942 and was able to engage in combat with all types of German aircraft, especially in turns, but was inferior to the Bf 109 in climb rate and the Bf 109 F in speed, which did not allow the type to effectively counter Bf 109 in vertical maneuvers.

The Yak-1 also had several design flaws: the main ones were fuel tank leaks and oil leaks from the propeller transmission, especially in aircraft with the M-105PF engine, which caused oil to splash onto the transparent part of the canopy, impairing visibility. There was also no canopy emergency release, which created the risk of its sliding part jamming in case of damage in combat, so pilots often preferred to fly with the cockpit open, believing that the loss of 10-15 km of speed was compensated by better visibility and safety in combat. The M-105PF engine also suffered from the same overheating problems that had occurred during testing, so it was necessary to carefully monitor the water temperature when climbing and to make horizontal turns every 2.5-3 km of altitude gained.

Nevertheless, pilots and technicians loved it: it was simple and easy to control in flight, accessible to pilots with little training and straightforward, and easy to repair in the field.

Used sources:

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

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

3. Materials from the site airwar.ru

Indicated stall speed in flight configuration: 155..171 km/h
Indicated stall speed in takeoff/landing configuration: 133..146 km/h
Dive speed limit: 720 km/h
Maximum load factor: 10.3 G
Stall angle of attack in flight configuration: 18 °
Stall angle of attack in landing configuration: 15.6 °
 
Maximum true air speed at sea level, engine mode - Nominal, 2550 RPM: 514 km/h
Maximum true air speed at 2000 m, engine mode - Nominal, 2700 RPM: 549 km/h
Maximum true air speed at 4000 m, engine mode - Nominal, 2700 RPM: 582 km/h
 
Service ceiling: 10200 m
Climb rate at sea level: 16.9 m/s
Climb rate at 3000 m: 15.0 m/s
Climb rate at 6000 m: 9.4 m/s
 
Maximum performance turn at sea level: 19.2 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 24.6 s, at 270 km/h IAS.
 
Flight endurance at 3000 m: 1.9 h, at 350 km/h IAS.
 
Takeoff speed: 160..190 km/h
Glideslope speed: 195..205 km/h
Landing speed: 135..145 km/h
Landing angle: 12 °
 
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 (2550 RPM) at sea level: 1240 HP
Maximum power in Nominal mode (2700 RPM) at sea level: 1210 HP
Maximum power in Nominal mode (2700 RPM) at 800 m: 1260 HP
Maximum power in Nominal mode (2700 RPM) at 2700 m: 1200 HP
 
Engine modes:
Nominal (unlimited time): 2550/2700 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: 2300 m
 
Empty weight: 2365 kg
Minimum weight (no ammo, 10% fuel): 2583 kg
Standard weight: 2932 kg
Maximum takeoff weight: 3170 kg
Fuel load: 304 kg / 408 l
Useful load: 805 kg
 
Forward-firing armament:
20mm gun "SsVAK", 120 rounds, 800 rounds per minute, nose-mounted
2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, synchronized
 
Bombs:
2 x 50 kg general purpose bombs "FAB-50sv"
2 x 104 kg general purpose bombs "FAB-100M"
 
Rockets:
Up to 6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg
 
Length: 8.5 m
Wingspan: 10 m
Wing surface: 17.15 m²
 
Combat debut: May 1942
 
Operation features:
- The engine has a two-stage mechanical supercharger which must be manually switched at 2300m 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 220 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 80 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.
- 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.
 
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 50%
- 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 66%
- combat: open 80%
 
4. Approximate fuel consumption at 2000 m altitude:
- nominal mode of engine operation: 7.4 l/min
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