Sikorsky S-67 Blackhawk

 

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.

 

 

Attribution

Attribution
Overview
Parent type *No Type assigned
Variant *No Variant assigned
Design authority Sikorsky Aircraft Div., United Aircraft and Transport Corporation
Primary manufacturer Sikorsky Aircraft Div., United Aircraft and Transport Corporation
Key Characteristics
Operational status No longer flying
Max gross weight (ground)   259 9,979 kg 22,000 lb
Crew 2
Seating arrangement Tandem
Configuration
VTOL type Helicopter
Compound type Lift
Lift configuration Single main rotor
Control device type Tail rotor
Features
Number of engines 2
Number of propulsors 0
Number of lift devices 1
Number of control devices 1
Milestones associated with the Sikorsky S-67 Blackhawk
1970 First flight of the Sikorsky S-67 Blackhawk

Sikorsky S-67 Blackhawk

 

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.

 

 

Attribution
Overall Dimensions
Overall height   258 4.95 m 16.3 ft
Overall length   259 22.58 m 74.1 ft
Overall width   258 18.90 m 62.0 ft
Note: All dimensions may be governed by the the diameter of an external rotor.
Airframe Dimensions
Airframe height   259 4.57 m 15.0 ft
Airframe length   259 19.74 m 64.8 ft
Airframe width 8.33 m 27.3 ft
Landing Gear Dimensions
Landing gear type Wheels (some retractable)
Landing gear base   258 11.02 m 36.2 ft
Landing gear track   258 2.13 m 7.0 ft
Cabin Dimensions
Cabin height  
Cabin length  
Cabin width  

Sikorsky S-67 Blackhawk

 

The intermediate (30 min. rating) is referred to as 'Military Power' in the reference

 

 

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Powerplant
Manufacturer General Electric Company
Powerplant designation T58-GE-5
Type Turbine
Normal Ratings (uninstalled, sea level, static)
Max. continuous power 933 kW 1,250 hp
Intermediate power 1,044 kW 1,400 hp
Maximum power  
Take-off power 1,119 kW 1,500 hp
 
OEI Ratings (uninstalled, sea level, static)
OEI Max. continuous power  
OEI Intermediate power  
OEI Contingency power  
OEI 30-second power  

Sikorsky S-67 Blackhawk

 

SH-3D main rotor head

 

 

Image coming soon!

Main Rotor Characteristics
Hub type   258 Fully articulated in flap and lag
Direction of rotation   167 Counterclockwise
Diameter   258 18.90 m 62.00 ft
RPM   258 195.9
Main Rotor Blade Characteristics
Blades per rotor   258 5
Blade chord   258 0.464 m 1.52 ft
Blade twist   258   -4.000 deg
Construction
Tip geometry  259 20 degrees swept
Main Rotor Derived Characteristics
Disk area 280.48 m² 3,019.2 ft²
Disk loading 35.58 kg/m² 7.287 lb/ft²
Solidity 0.0781
Note: disk loading is based on max gross weight (on ground) to help compare the widest range of aircraft.
Main Rotor Blade Derived Characteristics
Area per blade 4.38 m² 47.1 ft²
Blade tip speed 193.85 m/s 636.0 fps
Note: blade area is calculated as rotor radius times blade chord and ignores any root cut-out.

Sikorsky S-67 Blackhawk

 

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

 

 

Image coming soon!

Tail Rotor Characteristics
Hub type Articulated in flap only with 45 deg. pitch/flap coupling
Direction of rotation Unknown
Diameter 3.51 m 11.52 ft
RPM  
Configuration Pusher
Tail Rotor Blade Characteristics
Blades per rotor 5
Blade chord 0.186 m 0.61 ft
Blade twist 0.00 rad 0.0 deg
Construction  
Tail Rotor Derived Characteristics
Disk area 9.68 m² 104.2 ft²
Solidity 0.1690
Tail Rotor Blade Derived Characteristics
Area per blade 0.327 m² 3.52 ft²
Blade tip speed  

Sikorsky S-67 Blackhawk

 

NOTE: the performance data shown is for the aircraft in the standard, clean configuration and weights detailed below, at International Standard Atmosphere (ISA) sea-level conditions. Any deviation from these conditions will be defined in the general notes below, or in any references accompanying a specific data point.

 

S-67 Blackhawk performance

 

 
Weights
Maximum take-off weight 9,979 kg 22,000 lb
Empty weight   259 5,681 kg 12,525 lb
Useful load 4,298 kg 9,475 lb
Empty weight fraction 0.569
Limitations
Never exceed speed 370 km/h 200 kts
Max. level flight speed   259 324 km/h 175 kts
Service ceiling 5,180 m 16,995 ft
Normal Ratings (uninstalled, sea level, static)
Powerplant GE T58-GE-5
Number of engines   2
Max. continuous power 933 kW 1,250 hp
Intermediate power 1,044 kW 1,400 hp
Maximum power  
Take-off power 1,119 kW 1,500 hp
Note: all powers quoted are per engine.
Range and Endurance
Range (no reserve)   259 522 km 282 nm
Endurance (no reserve)  
Hover Performance
Hover ceiling IGE   259 2,957 m 9,700 ft
Hover ceiling OGE   259 1,981 m 6,500 ft
Climb Performance
Maximum rate of climb   259 10.2 m/s 2,000 fpm

Sikorsky S-67 Blackhawk

 

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Sikorsky S-67 Blackhawk

 

Forum Proceedings related to the Sikorsky S-67 Blackhawk

Aerodynamic Design Rationale for the Fan-in-Fin on the S-67 Helicopter
David R. Clark, Sikorsky Aircraft

 

Flight Investigation of Design Features of the S-67 Winged Helicopter
R. C. Dumond and D. R. Simon, Eustis Directorate, USAAMR&D Lab

 

Flight Tests to Develop the S-67 Blackhawk TM
R. L. McCutcheon, Sikorsky Aircraft Div.

 

 

Vertiflite articles related to the Sikorsky S-67

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Content from the AHS website related to the Sikorsky S-67

 

Downloadable files

 

Stratford Chapter Social Gathering, March 26 2014

 

 

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Articles from the Journal of the American Helicopter Society related to the Sikorsky S-67

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Articles from NASA Technical Reports Server related to the Sikorsky S-67

 

Patent information from the US Patent and Trademark Office related to the Sikorsky S-67

 

Google Books related to the Sikorsky S-67

Sikorsky S-67 Blackhawk

 

Overview

 

 

Layout

 

 

Miscellaneous

 

 

Sikorsky S-67 Blackhawk

Aircraft Notes

Ref. Author(s) Title Source Date Type
167 A.C. Ballauer and P. F. Sheridan The Twin-Engine BO-105 VERTIFLITE August 1969 August 1969 Periodical
  Good description of the overall vehicle
258 Richard M. McCutcheon S-67 Flight Test program Paper presented the 28th Annual National Forum of the American Helicopter Society May 1972 Meeting paper or Presentation
  Comprehensive description of the aircraft and it's flight test program
259 Art Linden The S-67 Blackhawk The Sikorsky Archives | Sikorsky product History May 2012 Website
  Comprehensive description of the aircraft and its design and development