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Yakovlev AIR-9
From 1933 Yakovlev and his design team developed a 2-seat low-wing monoplane sport aircraft with open cockpits, wooden wings, welded steel tube fuselage, powered by a Shvetsov M-11 engine. Fitted with landing flaps and automatic leading-edge slats, the AIR-9 design was submitted to a safe aircraft design competition, but was not proceeded with.
The original AIR-9 design was re-worked in 1934 to include enclosed cockpits, but dispensing with the automatic slats. The tandem cockpits were fitted with sliding canopies; the forward canopy slid rearwards over the fixed centre canopy section and the rear canopy slid forwards under the centre-section
The structure of the AIR-9 followed Yavovlev's previous designs with wooden plywood and fabric covered wings, welded steel tube fabric-covered fuselage and Duralumin fabric covered tail surfaces. The fixed spatted main undercarriage was supported by struts, later fitted with trousers as well as spats, with a fixed tail-skid or tailwheel (as exhibited at the 1935 Milan airshow)
The AIR-9bis, in later form, without cowling and with undercarriage strut trousers
The AIR-9 was powered by a single 100 hp (75 kW) Shvetsov M-11 five-cylinder air-cooled radial driving a fixed pitch 2-bladed wooden propeller, variously fitted with individual exhaust stacks, collector ring and Townend ring cowling.
In 1935 the AIR-9 was modified, or a second aircraft built, with a forward sloping windshield and re-designated AIR-9bis. The large number of variations in configuration suggest that there were more than one aircraft, but this cannot be confirmed.
The AIR-9bis in flight, pilotted by Piontkovskii
The AIR-9bis was displayed at the 1935 Paris and Milan airshows, and in 1937, was flown by I.N. Vishnevskaya and Ye.M. Mednikova to set a women's altitude record in the FAI Class C category.
The original open cockpit 2-seat low-wing monoplane sport aircraft design, with split flaps and automatic leading edge slats; not proceeded with.
The original design reworked with closed cockpits and other refinements but without automatic slats. At least one built, at some stage seen with racing number 31.
Further modifications prompted re-designation to AIR-9bis, introducing a forward sloping windshield and undercarriage trousers. One converted from the AIR-9 or possibly several new built aircraft, seen wearing racing number 32.
Engine: 1 × Shvetsov M-11, 75 kW (100 hp)
Propeller: 2-bladed wooden fixed pitch
Wingspan: 10.2 m (33 ft 6 in)
Wing area: 16.87 m2 (181.6 sq ft)
Length: 6.97 m (22 ft 10 in)
Empty weight: 495 kg (1,091 lb)
Max takeoff weight: 768 kg (1,693 lb)
Fuel capacity: 63.5 kg (140 lb) fuel; 17.5 kg (39 lb) oil
Maximum speed: 215 km/h (134 mph, 116 kn)
Landing speed: 65 km/h (40 mph; 35 kn)
Cruise speed: 195 km/h (121 mph, 105 kn)
Range: 695 km (432 mi, 375 nmi)
Service ceiling: 6,080 m (19,950 ft)
Time to 1,000 m / 3,300 ft): 4 minutes 48 seconds
Time to 3,000 m / 9,800 ft: 16 minutes 24 seconds
Take-off run: 80 m (260 ft)
Landing run: 90 m (300 ft)
Crew: 2
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