Technical data
Type UTI-6, NV-6
Function Aerobatic Trainer
Year 1940
Crew 1
Engine MG-11F
Power 165hp
Length 5.8m
Height ?m
Wingspan 7.0m
Wing area 14.0m2
Empty weight 560kg
Loaded weight 750kg
Wing Load (kg/m2) 53.6
Power load (kg/hp) 4.5
Speed at 0m 270km/h
Landing Speed 75km/h
Landing Roll 170m
Takeoff Roll 50m
Turn time ?sec
Range ?km
Flight Endurance 2.5h
Ceiling 4500m
Climb
1000m ?min
Payload
Fuel+Oil 80+20kg

UTI-6 (NV-6) by V.V.Nikitin

15k b/w NV-6 biplane as seen at "History of aircraft construction in the USSR", Vol.2 p.96

Aerobatic/trainer biplane with 8° swept upper wing and straight lower wing (carrying the ailerons). Engine was equipped with inverted flight carburetor designed by M.A.Kossov. NV-6 was of mixed construction: fuselage frame of chrome-molibdenium steel tubes, wing structure - wood, tail - aluminum. Fabric skin except the nose section. Center section of the fuselage and lower wing used those of the NV-1 aircraft. Estimated g-load was 13 (Ak).

Aircraft was built at OKB-30 in 1939 under Osoaviakhim order, but had to wait for more than a year for the engine to be delivered(December 1940). Flights were performed by V.V.Nikitin and V.V.Shevchenko during winter 1940/ 1941. Aircraft behaved well, but TsAGI did not allow official trials before static tests carried out.

Paperwork took a long time to finish, and on June 22, 1941 the war put the end to NV-6 development.


PredecessorsModifications

NV-1
None
ReferencesLinks
  • "History of aircraft construction in the USSR", Vol.2 p.96;
  • ....

  • Created October 28, 1999 Back to
    Main Gate