Yak-9T ser.1 / IL-2 Sturmovik: Great Battles
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Fighter
Yak-9T ser.1
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.

In order to retrain pilots for Yak aircraft, a two-seat training version of the Yak-7UTI began production in March 1941, but the shortage of fighters at the front naturally led to the idea of converting the training version into a single-seat combat version: this was the Yak-7. When in the summer of 1942 the opportunity arose to use aluminum alloys more widely, it was decided to create a lightweight version of the Yak-7DI (long-range fighter). Tests carried out from the end of June to the beginning of August confirmed the high performance of the new aircraft, which received the designation Yak-9.

The Yak-9 became the founder of the most numerous family of Soviet fighters during the Great Patriotic War. One of the first modifications of the aircraft was the Yak-9T version with improved armament.

The Yak-9T was a single-seat front-line fighter monoplane with a low wing of mixed design with a metal spar and retractable two-strut landing gear and tail wheel. Unlike the standard Yak-9, it was equipped with a large-caliber 11P (NS-37) motor cannon, and the installation of heavier and more powerful weapons required a number of significant design changes. The load-bearing frame of the fuselage was strengthened in the front section, and to accommodate the gun breech and keep the alignment within acceptable limits, the cockpit was moved rearwards, which slightly worsened the forward visibility during landing, but at the same time improved the visibility of the rear hemisphere during flight.

The engine remained the same M-105PF with a VISH-61P propeller. The engine developed a power of 1240 hp at take off and 1200 hp. at an altitude of 4000 m.

The 37 mm cannon was located in the camber of the engine cylinder block for firing through the hollow transmission shaft and propeller hub and was attached at two points: to the engine and the airframe. The barrel protruded from the propeller spinner, increasing the length of the aircraft. The UBS heavy machine gun, mounted above the engine on the left, was used for zeroing before opening fire from the cannon.

A total of 2,748 Yak-9Ts were built. With a normal takeoff weight, the Yak-9T's flight characteristics were similar to those of the Yak-9, slightly inferior in vertical maneuvering, but much superior in firepower: the mass of a second salvo from the Yak-9T was even greater than that of the Bf 110 and the Fw 109 A-8. The combat experience of the Yak-9T showed that its armament scheme was quite effective: hitting an enemy aircraft with a single shell usually resulted in its destruction, and the armor-piercing shells of the NS-37 cannon easily penetrated the armor of German tanks up to 30 mm thick at a distance of 500 m at an angle of up to 45°.

Compared to the Bf 109 G-2, armed with three cannons and two machine guns, the Yak-9T had an advantage in horizontal speed up to an altitude of 4,600 m. In vertical maneuvering, the Yak-9T maintained its advantage over the Bf 109G-2 up to an altitude of 3,000 m, at altitudes of 3,000 - 4,500 m their performance was about equal, and above that the advantage went to the Bf 109 G-2.

The higher efficiency of the 37 mm projectile and the limited ammunition load required the Yak-9T to be flown by highly qualified pilots, as it had to be fired in short bursts of one or two, at most three rounds. The limited ammunition load also meant that the Yak-9T had to be covered in combat by aircraft with lighter weapons, so these planes were used by mixed regiments and made up no more than 2/3 of their aircraft fleet.

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: 157..165 km/h
Indicated stall speed in takeoff/landing configuration: 139..145 km/h
Dive speed limit: 750 km/h
Maximum load factor: 10.5 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, 2550 RPM: 535 km/h
Maximum true air speed at sea level, engine mode - Nominal, 2700 RPM: 529 km/h
Maximum true air speed at 1850 m, engine mode - Nominal, 2700 RPM: 560 km/h
Maximum true air speed at 4000 m, engine mode - Nominal, 2700 RPM: 593 km/h
 
Service ceiling: 10250 m
Climb rate at sea level: 16.5 m/s
Climb rate at 3000 m: 13.5 m/s
Climb rate at 6000 m: 7.5 m/s
 
Maximum performance turn at sea level: 19.0 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 25.5 s, at 285 km/h IAS.
 
Flight endurance at 3000 m: 2.1 h, at 350 km/h IAS.
 
Takeoff speed: 170..200 km/h
Glideslope speed: 195..205 km/h
Landing speed: 140..150 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: 2200 m
 
Empty weight: 2470 kg
Minimum weight (no ammo, 10% fuel): 2631 kg
Standard weight: 3015 kg
Maximum takeoff weight: 3033 kg
Fuel load: 316 kg / 430 l
Useful load: 563 kg
 
Forward-firing armament:
37mm gun "NS-37", 30 rounds, 250 rounds per minute, nose-mounted
12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute, synchronized
 
Length: 8.5 m
Wingspan: 10 m
Wing surface: 17.15 m²
 
Combat debut: Summer 1943
 
Operation features:
- The engine has a two-stage mechanical supercharger which must be manually switched at 2000...2400m 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 airplane can only be trimmed in the pitch axis.
- 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.
- The canopy has no emergency release. In order to bail out, you must slow below 550 kph to open the canopy.
 
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 40%
- combat: open 80%
 
4. Approximate fuel consumption at 2000 m altitude:
- Cruise engine mode: 7.5 l/min
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