Mil V-16: Difference between revisions
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;Mi-16: The proposed VVS designation for the production V-16.<ref name="Gordon 2005"/> |
;Mi-16: The proposed VVS designation for the production V-16.<ref name="Gordon 2005"/> |
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==Specifications (V-16)== |
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General characteristics (Planned) |
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|genhide= |
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|crew=6 (pilot, copilot, flight engineer, electrician, navigator, radio operator) |
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|capacity=196 passengers<br/> |
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::::normal {{convert|20000|kg|lb|abbr=on}} |
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::::maximum {{convert|40000|kg|lb|abbr=on}} |
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|length m=37 |
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|span m=67 |
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|span note=across rotors |
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|height m=12.5 |
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|empty weight kg=69100 |
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|gross weight kg=97000 |
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|max takeoff weight kg=105000 |
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|fuel capacity= |
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|more general=<br/> |
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*'''Freight compartment:''' {{convert|28.15|*|4.4|*|4.4|m|ft|abbr=on}} |
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==References== |
==References== |
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{{commons category|Mil Helicopters}} |
{{commons category|Mil Helicopters}} |
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Revision as of 04:11, 9 December 2016
| V-16 | |
|---|---|
| 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.