Development was started by Northwest Polytechnic University in 1965, but was transferred to the Nanjing Aviation Institute.  Two prototypes and a static test article were made.  The first flight of the Yan'an-2 was on 4 September, 1975; alas, the helicopter never reached mass production.  A variant was developed in 1983 in which the main rotor material was changed from metal to composite.

A two-seater light helicopter, the Yan'an-2 fuselage was a semi-monocoque pod-and-boom construction on tricycle landing gear.

The aircraft never went into production.


Data on design, manufacture and status

Latest or last design authority: Nanjing University of Aeronautics and Astronautics
Originally designed by Northwestern Polytechnical University

Latest or last primary manufacturer: Nanjing University of Aeronautics and Astronautics
Originally manufactured by Northwestern Polytechnical University

Parent type: NUAA Yan-An 2

Aircraft status: No longer flying


Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 1-2

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height:  
Overall Length:  
Overall Width:  
Airframe Dimensions
Airframe Length: 8.00 m 26.2 ft
Airframe Width:  
Airframe Height:  
Landing Gear Dimensions
Landing Gear Base:  
Landing Gear Track:  
Cabin Dimensions
Cabin Internal Height:  
Cabin Internal Length:  
Cabin Internal Width:  

Weights and Performance

Data on aircraft weight and flight characteristics

Max Forward Speed: 190 km/h

Max Gross Weight (ground): 1,155 kg 2,546 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 1,155 kg 2,546 lb
Empty Weight:  
Useful Load:  
Empty Weight Fraction:  
Climb Performance
Max Rate of Climb:  
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Max Level Flight Speed:  
Never Exceed Speed:  
Service Ceiling:  
Range and Endurance
Max Range: 230 km 124 nm
Max Endurance:  

Engine Details

Aircraft powerplant (lift and/or propulsion)

Provided powerplant data is for uninstalled, sea level, static operations.

Number of engines: 1
Designation: ZEF HS-6C reciprocating
Manufacturer: Zhuzhou Engine Factory
Normal Ratings
Max continuous:  
Take-off / rated:  
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

Main Rotor Characteristics
Diameter: 10.00 m 32.81 ft
RPM: 372.7 rpm 372.7 rpm
Direction of Rotation: Clockwise
Hub Type: Fully articulated
Main Rotor Blade Characteristics
Blade Construction: Originally metal, replaced with composite material in 1983
Blade Chord: 0.254 m 0.83 ft
Blade Tip Geometry: Conventional
Blade Twist:  
Number of Blades: 3
Main Rotor Derived Characteristics
Disc Area: 78.54 m² 845.4 ft²
Disc Loading: 14.71 kg/m² 3.012 lb/ft²
Solidity: 0.0485
Main Rotor Blade Derived Characteristics
Blade area per blade: 1.27 m² 13.7 ft²
Tip Speed: 195.15 m/s 640.2 fps

Primary Control Device

Data on primary control devices such as tail rotors

Tail Rotor Characteristics
Diameter: 1.80 m 5.91 ft
Configuration: Unblocked
Direction of Rotation: Top blade fwd
RPM: 1920 rpm 1920 rpm
Tail Rotor Blade Characteristics
Number of Blades: 2
Blade Construction: Glass-reinforced plastic (GRP)
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area: 2.54 m² 27.4 ft²
Tail Rotor Blade Derived Characteristics
Tip Speed: 180.92 m/s 593.6 fps
Blade Area (per blade):  

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