The mass production of the new fighter and its arrival to the frontline units begun only in 1943. In combat, the Yak-9 proved itself as very maneuverable and easy to control fighter, earning the love and respect of many Soviet pilots along with volunteer French from the Normandie Niemen fighter regiment.
In addition to Quick Mission Builder and Multiplayer modes, you can fly it in Career mode during Battle of Kuban timeframe.
- Armament: 20mm gun "ShVAK", 120 rounds, 800 rounds per minute and 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute.
- Length: 8.5 m
- Wingspan: 10 m
- Wing surface: 17.15 m²
Modifications
- Landing light for night flights (2 kg weight increase, minor speed loss).
- Fixed loop radio compass RPK-10 (10 kg weight increase, minor speed loss).
- PBP-1A reflector gunsight (0.5 kg weight increase).
- Rearview mirror (1 kg weight increase).
Skins
- Standard paint scheme.
- Lt.-Col. A.A. Matveev, 275th IAD, 1943.
- Fleeing Goebbels picture. Major I.N. Stepanenko, Summer 1943.
- Guards Captain S.A. Mikoyan, 32nd GIAP. The inscription 'For Volodya' means he is avenging his killed brother V.A. Mikoyan.
- Eagle in a circle picture. Lieutenant G.I. German, 42nd IAP, 240th IAD, 1943.
- 'For brother' dedicatory inscription. Major A.N. Kiloberidze, 65th GIAP, October 1944.
- Jaws picture on the front. A.A. Barsht, 118th OKRAP (separate spotting-and-reconnaissance aviation regiment) squadron commander, 1st Ukrainian Front, Late 1944.
- Lt.-Col. M.V. Avdeev, 6th GIAP, May 1944.
- Guards symbol. Captain M.I. Grib, 6th GIAP, May 1944.
- 'For Motherland' dedicatory inscription. Captain N.F. Denchik, 64th GIAP, early 1944.
- Standard grey camo.
Technical details
Indicated stall speed in flight configuration: 152..160 km/h
Indicated stall speed in takeoff/landing configuration: 136..141 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: 537 km/h
Maximum true air speed at sea level, engine mode - Nominal, 2700 RPM: 529 km/h
Maximum true air speed at 1700 m, engine mode - Nominal, 2700 RPM: 563 km/h
Maximum true air speed at 3800 m, engine mode - Nominal, 2700 RPM: 594 km/h
Service ceiling: 10500 m
Climb rate at sea level: 18.5 m/s
Climb rate at 3000 m: 15.8 m/s
Climb rate at 6000 m: 9.0 m/s
Maximum performance turn at sea level: 17.5 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 22.5 s, at 285 km/h IAS.
Flight endurance at 3000 m: 2.1 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 the 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: 2254 kg
Minimum weight (no ammo, 10% fuel): 2549 kg
Standard weight: 2841 kg
Maximum takeoff weight: 2858 kg
Fuel load: 324 kg / 440 l
Useful load: 604 kg
Combat debut: November 1942
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 airplane has 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 airplane has differential pneumatic wheel brakes with a 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 the left and right wing fuel tanks, outside of the cockpit. Less than 25l of fuel remaining in the wing tanks or the central feeder tank (10 liters capacity) are not measured.
- The canopy has no emergency release. In order to bail out, you must slow below 550 kph to open the canopy.
