Nikitin UTI-6

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Nikitin UTI-6
f2
Type: Trainer aircraft
Design country:

Soviet Union 1923Soviet Union Soviet Union

Manufacturer:

Nikitin

First flight:

December 1940

Commissioning:

-

Production time:

1939-1940

Number of pieces:

1

The Nikitin UTI-6 ( Russian: Никитин УТИ-6 ) was a small aerobatic trainer aircraft. The single-handled biplane was designed by the Soviet designer W. W. Nikitin . The order was placed in 1939 by OSSOAWIACHIM and carried out by OKB-30 .

history

Often referred to as the NW-6, this aircraft was completed in December 1940 and flown in by the pilot and employee W. W. Shevchenko , as well as by Nikitin himself, because the modified engine specially designed for this aircraft was not yet available. In order to be able to use it as a training and training aircraft for the pilots of the Soviet air force , it had to be suitable for aerobatics. This was ensured by the particular strength of the airframe and the wing construction, which were partly taken over from the NW-1 . Last but not least, the engine had a special carburetor , which ensured that the engine could be supplied with fuel in every flight position, including the supine position .

In order to confirm the required load values, the corresponding static tests had to be carried out at the ZAGI . These dragged on until the attack on the Soviet Union began . Despite the very good flight characteristics, there was no time to further develop the design. In the series of Nikitin developments, the UTI-6 was the second smallest machine after the NW-1 and, in terms of its demands, ideally suited for "higher" aerobatics. Because of its small dimensions, the pilots also called this aircraft a "flying toy".

construction

The UTI-6 biplane was built using a composite construction method. The fuselage was about 1.50 meters longer than that of the NW-1 and was assembled in one piece from welded steel tubing, which was partially clad with aluminum sheet up to the rear of the open pilot's cabin. The rear part of the fuselage was covered with plywood, which was then covered with linen. Finally, the covering was given a weatherproof paint. A similar construction also applied to the wings (wing spars made of steel, ribs made of aluminum and the cladding made of plywood with linen cloth). The upper wing was not placed on the fuselage, but was connected to the fuselage by four struts in the so-called Parasol design (also known as the canopy design). This gave the pilot an unobstructed view to the front below the upper wing.

Both wings were connected to each other by a stable, streamlined I-stem, which was also braced crosswise to the fuselage with wire ropes. This biplane still had one special feature: the trailing edge of the upper wing had the same sweep of 8 degrees as the leading edges of both surfaces. The result was a rare combination of a straight and a swept wing. The ailerons were only on the lower wing. The aircraft had a fixed landing gear, the wheels of which were clad in a streamlined manner by appropriate wheel covers. A MG-11F engine with 165 hp was used as the drive . A total of around 100 kg of lubricant and fuel could be carried.

Technical specifications

Parameter Data
crew 1
length 5.80 m
span 7.00 m
Wing area 14.00 m²
payload 190 kg
Empty mass 560 kg
Takeoff mass 750 kg
Wing loading 53.6 kg / m²
Landing speed 75 km / h
Top speed 270 km / h
Service ceiling 4500 m
Range 300 km
Flight duration 2.5 h
Engine MG-11F
power 123 kW (165 hp)
Armament -
Other equipment unknown

See also

literature

Web links