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At a glance
Measured figures
PC-9M · Only the source-declared variant PC-9M · PC-9M
Single source10.14 m (33 ft 3 in)[source]Only the source-declared variant PC-9M
Iak 52 · Length
Single sourceConfiguration
| Specification | PC-9M | Yakovlev Yak-52 |
|---|---|---|
| Variant description | PC-9M[source]Only the source-declared variant PC-9M This version was introduced in 1997 as the new standard model. It has an enlarged dorsal fin in order to improve longitudinal stability, modified wingroot fairings, stall strips on the leading edges as well as new engine and propeller controls.[source]Only the source-declared variant PC-9M | — |
| Stall speed | 143 km/h (89 mph, 77 kn) EAS flaps and gear up, 128 km/h (80 mph; 69 kn) flaps and gear down[source]Only the source-declared variant PC-9M | 85–90 km/h (53–56 mph, 46–49 kn) flaps down, engine idling[source] |
| Endurance | four hours and 30 minutes[source]Only the source-declared variant PC-9M | — |
7.745 m (25 ft 5 in)[source]
Empty; PC-9M · Only the source-declared variant PC-9M · PC-9M
Single sourceGross; PC-9M · Only the source-declared variant PC-9M · PC-9M
Single source1,725 kg (3,803 lb)[source]Only the source-declared variant PC-9M
2,350 kg (5,181 lb)[source]Only the source-declared variant PC-9M
3,200 kg (7,055 lb) A view of the interior of the cockpit of a Pilatus PC-9 aircraft.[source]Only the source-declared variant PC-9M
Empty; Iak 52 · Empty weight
Single sourceMaximum take-off; Iak 52 · Max takeoff weight
Single sourceCruise; PC-9M · Only the source-declared variant PC-9M · PC-9M · at 7,620 m (25,000 ft)
Single sourceMaximum; PC-9M · Only the source-declared variant PC-9M · PC-9M
Single source593 km/h (368 mph, 320 kn)[source]Only the source-declared variant PC-9M
556 km/h (345 mph, 300 kn) at 7,620 m (25,000 ft)[source]Only the source-declared variant PC-9M
Cruise; Iak 52 · at 1,000 m (3,300 ft) (econ cruise)
Single sourceMaximum; Iak 52 · at sea level
Single sourcePC-9M · Only the source-declared variant PC-9M · PC-9M · 1 × Pratt & Whitney Canada PT6A -62 turboprop
Single sourcePC-9M · Only the source-declared variant PC-9M · PC-9M · flat-rated at 950 shp
Single source1 × Pratt & Whitney Canada PT6A -62 turboprop, 857 kW (1,149 hp) flat-rated at 708 kW (950 shp)[source]Only the source-declared variant PC-9M
Iak 52 · 1 × Vedeneyev M-14P nine-cylinder radial engine
Single source1 × Vedeneyev M-14P nine-cylinder radial engine , 270 kW (360 hp)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| g limits |
|---|
+ 7.0 g to −3.5 g[source]Only the source-declared variant PC-9M |
+7/-5[source] |
| Take-off distance over 50 ft (15 m) obstacle at sea level | 1,280 ft (391 m)[source]Only the source-declared variant PC-9M | — |
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| Landing distance over 50 ft (15 m) obstacle at sea level | 2,295 ft (700 m)[source]Only the source-declared variant PC-9M | — |
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| Hardpoints | seven hardpoints, 3 under each wing, inner two rated at 250 kg (550 lb), outer rated at 110 kg (240 lb)[source]Only the source-declared variant PC-9M Hardpoints: seven hardpoints, 3 under each wing, inner two rated at 250 kg (550 lb), outer rated at 110 kg (240 lb)[source]Only the source-declared variant PC-9M | — |
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| Manufacturer | Pilatus Aircraft[source]Manufacturer of the source-named PC-9M only; no base PC-9 geometry or variant feature inherited. | Yakovlev Aerostar[source] |
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| Country of origin | Switzerland[source]Inventory Origin column; table 1, row 21, cell 2; revision 1376580369 Switzerland[source]Inventory Origin column; table 1, row 14, cell 2; revision 1372375479 Switzerland[source]Inventory Origin column; table 2, row 19, cell 2; revision 1365898407 | — |
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| Type | — | Trainer , COIN[source] |
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| Status | — | Operational[source] |
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| Primary users | — | Soviet Air Force DOSAAF Ukrainian Army Aviation[source] |
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| Manufactured | — | 1978–1998[source] |
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| Introduction date | — | 1979[source] |
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| First flight | — | 1976[source] |
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| Developed from | — | Yakovlev Yak-50[source] |
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| Developed into | — | Yakovlev Yak-53[source] |
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| Airfoil | — | Clark YN[source] |
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| Fuel capacity | — | 122 L (32 US gal; 27 imp gal)[source] |
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| Propellers | — | 2-bladed V-530TA-D35 constant-speed propeller , 2.40 m (7 ft 10 in) diameter[source] |
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| Never exceed speed | — | 360 km/h (220 mph, 190 kn)[source] |
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| Time to altitude | — | 15 min to 4,000 m (13,000 ft)[source] |
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| Role | — | Soviet primary trainer aircraft[source] |
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| National origin | — | Soviet Union[source] |
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| Source measurement | — | A descendant of the single-seat competition aerobatic Yakovlev Yak-50 , the all-metal Yak-52 is powered by a 268 kW (360 hp) Vedeneyev M14P nine-cylinder radial engine .[source]Yakovlev Yak-52 · Design and development; only the objects and conditions stated in this passage The aircraft has fuel and oil systems permitting inverted flight for as long as two minutes. The engine drives a two-bladed counter-clockwise rotating, variable pitch, wood and fiberglass laminate propeller.[source]Yakovlev Yak-52 · Design and development; only the objects and conditions stated in this passage At 998 kg (2,200 lb) empty weight, the Yak-52 has been used in international aerobatic competition up to the Advanced level. It is stressed to +7 and –5 Gs, rolls (to the right) at well more than 180 degrees/second (measured up to 352 degrees/second to the right), and is capable of every manoeuvre in the Aresti catalog .[source]Yakovlev Yak-52 · Design and development; only the objects and conditions stated in this passage A number of "westernised" versions of the Yak-52 are now produced. The replacement of the existing Soviet avionics , fitting of a three-blade propeller and the M14PF 298 kW (400 hp) upgrade to the usual 360 hp M14P engine, and conversion to conventional "tail-dragger" landing gear (Yak-52TD) are some of the modifications made to the standard aircraft. There is also a factory-produced Yak-52TW tail-dragger version by Aerostar. The TW has an extra 120 L (32 US gal) of fuel capacity in two extra wing tanks, the M14PF engine designated & three blade propeller, an electric start, and modern instruments.[source]Yakovlev Yak-52 · Design and development; only the objects and conditions stated in this passage On 16 April 2004, a modernised variant Yak-52M was flown in Russia. It is fitted with modernised M-14Kh engine, three-blade propeller, and other modifications.[source]Yakovlev Yak-52 · Design and development; only the objects and conditions stated in this passage Two-seat primary trainer aircraft, powered by a 360-hp (268-kW) Vedeneyev M-14P nine-cylinder radial piston-engine.[source]Yakovlev Yak-52 · Variants; only the objects and conditions stated in this passage Yak-52M[source]Yakovlev Yak-52 · Variants; only the objects and conditions stated in this passage Modified Yak-52 with more powerful M-14PF engine and a tailwheel configuration by Termikas Ltd in Lithuania. Modifications include a set of wings with integrated aerobatic and ferry tanks (total capacity 230 litres), and allow complete retraction (no portions of the gear/main strut extend below wing structure). Bulletin 60 (strong joint fittings of the main spar) and Bulletin 107 (steel strap on the main spar installed) also completed at modification.[source]Yakovlev Yak-52 · Variants; only the objects and conditions stated in this passage In late 2025, the World Air Forces publication by FlightGlobal , which tracks the aircraft inventories of world's air forces and publishes its counts annually, published the World Air Forces 2026 report. According to that report, the only military operator of Yak-52 in the world is the Romanian Air Force with 14 aircraft.[source]Yakovlev Yak-52 · Operators; only the objects and conditions stated in this passage Length: 7.745 m (25 ft 5 in)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Wingspan: 9.30 m (30 ft 6 in)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Height: 2.70 m (8 ft 10 in)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Wing area: 15.00 m 2 (161.5 sq ft)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Empty weight: 1,015 kg (2,238 lb)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Max takeoff weight: 1,305 kg (2,877 lb)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Powerplant: 1 × Vedeneyev M-14P nine-cylinder radial engine , 270 kW (360 hp)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Propellers: 2-bladed V-530TA-D35 constant-speed propeller , 2.40 m (7 ft 10 in) diameter[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Maximum speed: 285 km/h (177 mph, 154 kn) at sea level[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Cruise speed: 190 km/h (120 mph, 100 kn) at 1,000 m (3,300 ft) (econ cruise)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Stall speed: 85–90 km/h (53–56 mph, 46–49 kn) flaps down, engine idling[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Never exceed speed : 360 km/h (220 mph, 190 kn)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Range: 550 km (340 mi, 300 nmi) at 500 m (1,600 ft)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Service ceiling: 4,000 m (13,000 ft)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Rate of climb: 5.00 m/s (985 ft/min)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage Time to altitude: 15 min to 4,000 m (13,000 ft)[source]Yakovlev Yak-52 · Specifications (Iak 52); only the objects and conditions stated in this passage |
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