СКБ-2 МАИ: Х-1
SKB-2 MAI: Kh-1

General data

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Names and dates
Market original model designation
Х-1
Market model designation (english translation or spelling)
Kh-1
Project start date
1967
Date of prototype completion
1969
Country of manufacture
Russia
People involved
G. Kuznetsov {Г. Кузнецов}Design engineer
M. Fedotov {М. Федотов}Design engineer
A. Shugaev {А. Шугаев}Design engineer
A. Krasnikov {А. Красников}Design engineer
Config info
Rotorcraft typeCompound helicopter
Weights
Maximum Takeoff Weight (MTOW)
240
kg
Manufacturers empty weight (MEW)
110
kg
Main rotor
Drive type
Tip jets
Prerotation type
Pneumatic
Propeller
Mode
Pushing
Powerplant
Engine model
МТ-8
Engine model (english translation or spelling)
MT-8
Engine type (System no.: 1)
Piston
Engine type (System no.: 2)
Rocket
Engine type (System no.: 3)
Rocket
Number of engines
3
Total maximum power
72
HP
Fuel system
Fuel tank capacity
30
l
Average fuel consumption [volumetric]
10
l/h
Performance
Maximum horizontal flight speed (Vh)
115
km/h
Minimum speed
40
km/h
Best rate of climb (option 1)
11
m/s
Best rate of climb (option 2)
2
m/s
Maximum service ceiling (option 1)
3400
m
Maximum service ceiling (option 2)
2000
m
Maximum range
200
km
Maximum flight endurance
3
h
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