The aircraft was designed as a low-cost tactical helicopter demonstrator, based around the rotors, engines, hydraulic/electrical systems, and drive train of the S-61/H-3 series aircraft. It was a "semi-compund" design in that it was equipped with a lifting wing to off-load the rotor in high speed flight, but did not feature any auxiliary propulsion systems.

The main wheels were fully retractable but the tail wheel was fixed.


Data on design, manufacture and status

Design authority: Sikorsky Aircraft Division, United Aircraft and Transport Corporation

Primary manufacturer: Sikorsky Aircraft Division, United Aircraft and Transport Corporation

Parent type: No type defined

Aircraft status: No longer flying


Primary flight and mechanical characteristics

VTOL type: Helicopter

Compound type: Lift

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 2

Crew seating: Tandem

Landing gear: Wheels (some retractable)

Layout and Dimensions

Data on aircraft size

The S-67 was intended to field a thermally- and acoustically-insulated troop compartment for six troops, with access provided through a door on the left side of the fuselage.

Overall Dimensions
Overall Height: 4.95 m 16.3 ft
Overall Length: 22.58 m 74.1 ft
Overall Width: 18.90 m 62.0 ft
Airframe Dimensions
Airframe Length: 19.74 m 64.8 ft
Airframe Width: 8.33 m 27.3 ft
Airframe Height: 4.57 m 15.0 ft
Landing Gear Dimensions
Landing Gear Base: 11.02 m 36.2 ft
Landing Gear Track: 2.13 m 7.0 ft
Cabin Dimensions
Cabin Internal Height:  
Cabin Internal Length:  
Cabin Internal Width:  

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground): 9,979 kg 22,000 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 9,979 kg 22,000 lb
Empty Weight: 5,681 kg 12,525 lb
Useful Load: 4,298 kg 9,475 lb
Empty Weight Fraction: 0.569
Climb Performance
Max Rate of Climb: 10 m/s 2,000 fpm
Hover Performance
Hover Ceiling IGE: 2,957 m 9,700 ft
Hover Ceiling OGE: 1,981 m 6,500 ft
Max Level Flight Speed: 324 km/h 175 kts
Never Exceed Speed: 370 km/h 200 kts
Service Ceiling: 5,180 m 16,995 ft
Range and Endurance
Max Range: 522 km 282 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: GE T58-GE-5 turbine
Manufacturer: General Electric Company
Normal Ratings
Max continuous: 933 kW 1250 hp
Take-off / rated: 1119 kW 1500 hp
Intermediate: 1044 kW 1400 hp
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

SH-3D main rotor head

Main Rotor Characteristics
Diameter: 18.90 m 62.00 ft
RPM: 195.9 rpm 195.9 rpm
Direction of Rotation: Counterclockwise
Hub Type: Fully articulated in flap and lag
Main Rotor Blade Characteristics
Blade Construction:
Blade Chord: 0.464 m 1.52 ft
Blade Tip Geometry: 20 degrees swept
Blade Twist: -0.070 rad -4.000 deg
Number of Blades: 5
Main Rotor Derived Characteristics
Disc Area: 280.48 m² 3019.2 ft²
Disc Loading: 35.58 kg/m² 7.287 lb/ft²
Solidity: 0.0781
Main Rotor Blade Derived Characteristics
Blade area per blade: 4.38 m² 47.1 ft²
Tip Speed: 193.85 m/s 636.0 fps

Primary Control Device

Data on primary control devices such as tail rotors

SH-3D tail rotor hub. NACA 0012 tail blade airfoil section.

Tail Rotor Characteristics
Diameter: 3.51 m 11.52 ft
Configuration: Pusher
Direction of Rotation: Unknown
Tail Rotor Blade Characteristics
Number of Blades: 5
Blade Construction:  
Blade Chord: 0.186 m 0.61 ft
Blade Twist: 0.00 rad 0.0 deg
Tail Rotor Derived Characteristics
Disc Area: 9.68 m² 104.2 ft²
Solidity: 0.1690
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade): 0.327 m² 3.52 ft²

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