Mil V-16
V-16 | |
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General information | |
Manufacturer | Mil |
The Mil V-16 was a Soviet heavy cargo/transport helicopter project of the late 1960s. The original scheme described a heavy side-by-side twin-rotor aircraft with two soloviev D-25VF gas turbine engines below six-bladed rotors at the tips of heavily supported wings on each side of the fuselage and tricycle-type landing gear, with both rear landing wheels mounted below the wings while the front wheel was located below the cockpit.
A sample of V-16 has been on show at the Le Bourget-Paris "Salon de l'Aviation" in June, 1971.
Variants
- V-16
- Proposed ultra-heavy version of the V-12, intended to lift 40,000 to 50,000 kg (88,000 to 110,000 lb). Originally envisaged in a three rotor layout, powered by six Soloviev D-25VF engines, but reverted to a two-rotor system similar to the V-12 powered by two large gas generators supplying a single large low pressure free-turbine driving a main gearbox each.[1]
- Mi-16
- The proposed VVS designation for the production V-16.[1]
Specifications (V-16)
|genhide=
|crew=6 (pilot, copilot, flight engineer, electrician, navigator, radio operator)
|capacity=196 passengers
- normal 20,000 kg (44,000 lb)
- maximum 40,000 kg (88,000 lb)
|length m=37
|span m=67
|span note=across rotors
|height m=12.5
|empty weight kg=69100
|gross weight kg=97000
|max takeoff weight kg=105000
|fuel capacity=
|more general=
- Freight compartment: 28.15×4.4×4.4 m (92.4×14.4×14.4 ft)
- ^ a b Gordon, Yefim; Dimitriy and Sergey Komissarov (2005). Mil's heavylift helicopters : Mi-6, Mi-10, V-12 and Mi-26. Red Star. Vol. 22 (2nd ed.). Hinckley: Midland Publishing. ISBN 1-85780-206-3.