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Yakolev Yak-52



The Yakolev Yak-52 is a two-seater tandem low wing civil and military aerobatic trainer aircraft with semi-retractable tricycled landinggear. Development of the Yakolev Yak-52, originally known Yak-50U, started in 1973 as a successor of the Yakolev Yak-18 training aircraft. The Yakolev 52 was designed by the Yakolev Design Bureau as a trainer version of the single-seat Yak-50. The prototype was flown first in 1974. Production was initiated in 1976 at the Intreprinderea de Avioane Bacau factory in Bacau, Romania and production of the Yak-52 started in 1977.




The Romanian prototype Yak-52 was flown first in May 1978 and deliveries started the same year. The IAK-52 airplane is equipped with a 360 hp Ivchenko Vedeneyev M-14P nine cylinder, air-cooled radial piston engine. The 400 hp M14PF can also be fitted. The Yak is all-metal, fully aerobatic machine with an inverted fuel system, and features semi retractable tricycle landing gear.  As an aircraft with excellent performance and +7/-5 G limits with two pilots and full fuel, the Yak-52 enables training from basic to unlimited level.




The Yak-52 was used in the Soviet Union as a basic military trainer as well as primary and advanced aerobatic trainer. A vast majority is in use with the Russian DOSAAF Clubs. The I.Av. Bacau was renamed Aerostar S.A. in 1991. Over 1800 have been produced starting with series-production in 1979. At the peak of production 150 aircraft were manufactured per year. Aerostar in Bacau, Romania as of 2009, was still producing the Yak-52 in limited numbers on request. The models were the Yak-52W, an upgraded derivative with Western instruments, radio, electrical etc. and the tail wheel version Yak-52TW.

Yak 52 TW



Engine: Vedeneyev Ivchyenko M-14P, 360 hp
Crew: 2
Height: 2.7 m
Length: 7.745 m
Wing span: 9.3 m
Wing area: 15 sq. m
Dihedral: 2 degrees
Wing incidence: 2 degrees
Propeller diameter: 2.4 m (V530TA-D35 constant speed propeller)
Wheel track: 2.715 m
Dry weight: 1035 kg
Maximum takeoff weight: 1315 kg
Maximum landing weight: 1315 kg
Weight of crew with parachutes: 180 kg
Fuel weight: 90 kg
Oil weight: 10 kg
Maximum fuel load: 120 L
Maximum oil load: 16 L
C of G limits (%): 17.5 - 27.0
Maximum level airspeed (at altitude 1000 m): 270 km/h
Range (10% fuel reserve at 190 km/h): 465 km (2 h 30 min)
Takeoff roll: 180 - 200 m
Landing roll: 330 m
Stall speed, engine at idle - erect flight, clean: 120 km/h
Stall speed, engine at idle - flaps, gear down: 110 km/h
Stall speed, engine at idle - inverted: 150 km/h
Approach speed: 160 km/h
Cruise 70%: 130 kt / 60 lt/hr.
Touchdown speed: 115 - 120 km/h
Takeoff speed: 120 km/h
Climb speed: 170 km/h
ROC: 1800 fpm.
Never exceed speed (VNE): 420 km/h
Maximum manoeuvring speed: 360 km/h
G limits: +7/-5
Maximum gear extended speed: 200 km/h
Maximum flaps extended speed: 170 km/h
Minimum fuel qty for aerobatics: 24 L
Maximum inverted flight time: 2 min (followed by at least 3 min of erect flight)
Maximum oil load for cross-country: 16 L
Maximum oil load for aerobatics: 10 L
Minimum oil load: 8 L

Yak 52TW

Engine: 400 HP
Prop: MTV-9-B/260-29


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