The RASCAL JUH-60A is a research and technology demonstrator aircraft developed by the U.S. Army and NASA as an airborne laboratory.

RASCAL stands for Rotorcraft Aircrew Systems Concepts Airborne Laboratory. The base platform is a UH-60A. The aircraft has been used in investigations of advanced, integrated control concepts for achieving high levels of agility and maneuverability, and guidance technologies, employing computer/sensor-aiding, designed to assist the pilot during low-altitude flight in conditions of limited visibility.

Source: “Rotorcraft In-Flight Simulation Research at NASA Ames Research Center: A Review of the 1980's and plans for the 1990’s”,  Aiken, Edwin W., Hindson, William S., Lebacqz, J. Victor, Denery, Dallas G., Eshow, Michelle M., NASA-TM-103873, Aug 01, 1991


Data on design, manufacture and status

Design authority: Sikorsky Aircraft Corp.

Primary manufacturer: Sikorsky Aircraft Corp.

Parent type: Sikorsky S-70/H-60

Aircraft status: In development


Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 0-1

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height: 5.16 m 16.9 ft
Overall Length: 19.79 m 64.9 ft
Overall Width: 16.38 m 53.7 ft
Airframe Dimensions
Airframe Length: 15.19 m 49.8 ft
Airframe Width: 4.37 m 14.3 ft
Airframe Height: 3.76 m 12.3 ft
Landing Gear Dimensions
Landing Gear Base: 8.84 m 29.0 ft
Landing Gear Track: 2.48 m 8.1 ft
Cabin Dimensions
Cabin Internal Height: 1.37 m 4.5 ft
Cabin Internal Length: 3.84 m 12.6 ft
Cabin Internal Width: 2.35 m 7.7 ft

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground):  
Max Gross Weight (airborne):  
Max Take-off Weight:  
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: 296 km/h 160 kts
Never Exceed Speed:  
Service Ceiling:  
Range and Endurance
Max Range:  
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 T700-GE-700 turbine
Manufacturer: GE Aviation
Normal Ratings
Max continuous:  
Take-off / rated:  
Intermediate: 1146 kW 1536 hp
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

Airfoil sections: SC1095 SC1094R8

Main Rotor Characteristics
Diameter: 16.36 m 53.67 ft
RPM: 258.0 rpm 258.0 rpm
Direction of Rotation: Counterclockwise
Hub Type: Fully articulated, with elastomeric bearings
Main Rotor Blade Characteristics
Blade Construction: Titanium spar blade with 2 cambered airfoil sections in 3 sections
Blade Chord: 0.527 m 1.73 ft
Blade Tip Geometry: 20 deg aft swept
Blade Twist: -0.314 rad -18.000 deg
Number of Blades: 4
Main Rotor Derived Characteristics
Disc Area: 210.15 m² 2262.1 ft²
Disc Loading:  
Solidity: 0.0821
Main Rotor Blade Derived Characteristics
Blade area per blade: 4.31 m² 46.4 ft²
Tip Speed: 220.97 m/s 725.0 fps

Primary Control Device

Data on primary control devices such as tail rotors

Tail rotor is canted, enabling tail rotor thrust to provide a vertical thrust component

Tail Rotor Characteristics
Diameter: 3.35 m 11.00 ft
Configuration: Tractor
Direction of Rotation: Top blade aft
RPM: 1214 rpm 1214 rpm
Tail Rotor Blade Characteristics
Number of Blades: 4
Blade Construction:
Blade Chord: 0.247 m 0.81 ft
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area: 8.83 m² 95.0 ft²
Solidity: 0.1875
Tail Rotor Blade Derived Characteristics
Tip Speed: 213.05 m/s 699.0 fps
Blade Area (per blade): 0.414 m² 4.46 ft²

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