The S.O.1221S Djinn was the twin-seat production version of the SO.1220 that had been flown originally to evaluate the cold jet method of powering the main rotor blades. In many references it is referred to as the Sud SO.1221 as Sud took over responsibility for the type after taking over SNCASO.

The primary operator was the French Aviation Légère de l'Armée de Terre with a small number operated by the Federal German Heeresfligerei.


Data on design, manufacture and status


Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Rudder

Crew required: 1

Crew seating: Side-by-side

Landing gear: Skids

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height:  
Overall Length:  
Overall Width:  
Airframe Dimensions
Airframe Length:  
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

Cruise Speed: 62 mph (99.7793 km/h)

Max Gross Weight (ground): 800 kg 1,764 lb
Max Gross Weight (airborne): 800 kg 1,764 lb
Max Take-off Weight: 800 kg 1,764 lb
Empty Weight: 315 kg 694 lb
Useful Load: 485 kg 1,070 lb
Empty Weight Fraction: 0.393
Climb Performance
Max Rate of Climb:  
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Max Level Flight Speed:  
Never Exceed Speed:  
Service Ceiling: 4,499 m 14,760 ft
Range and Endurance
Max Range: 180 km 97 nm
Max Endurance:  

Engine Details

Aircraft powerplant (lift and/or propulsion)

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

Number of engines: 2
Designation: Turbomeca Palouste IV turbine
Manufacturer: Turbomeca
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

The rotor blades are driven by compressed air, passing from the turbogenerator engine through ducted channels inside the rotor shaft and twin rotor blades to ejectors at the rotor tips. The tip jets operate almost like ramjets, but without the bulky combustion chambers needed by ramjets. The compressed air from the gas turbine engine is warm enough to eliminate the need for other means of de‑icing the blades.

Main Rotor Characteristics
Diameter: 10.01 m 32.83 ft
Direction of Rotation: Counterclockwise
Hub Type:
Main Rotor Blade Characteristics
Blade Construction:
Blade Chord:  
Blade Tip Geometry:
Blade Twist:  
Number of Blades: 2
Main Rotor Derived Characteristics
Disc Area: 78.66 m² 846.7 ft²
Disc Loading: 10.17 kg/m² 2.083 lb/ft²
Main Rotor Blade Derived Characteristics
Blade area per blade:  
Tip Speed:  

Primary Control Device

Data on primary control devices such as tail rotors

Tail Rotor Characteristics
Configuration: Unknown
Direction of Rotation: Unknown
Tail Rotor Blade Characteristics
Number of Blades:  
Blade Construction: N/A
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area:  
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade):  

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Related Public Resources

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