The X-100 was built primarily to flight test Curtiss-Wright's concept of using propeller "radial force" instead of wing lift for conventional flight. This phenomenon produces a large force at right angles to the airflow as the propeller angle of attack is increased. The X-100 used a 860 bhp fuselage-mounted Lycoming YT53-L-1 driving cross-shafts for the 10 ft diameter tilting fiberglass propellers at the wingtips. At the rear of its 24 ft fuselage, engine exhaust was used for pitch and yaw control in hover; roll control was provided by differential propeller pitch. Wingspan was 16 ft and gross weight was 3,500 lb.

The X-100 first hovered in free flight in September 1959, and made its first short take-off and landing flight on March 1960. Its first (and only) transition from vertical to horizontal was performed in April 1960. Control in hover was weak due to the low exhaust gas velocity. Testing continued until October 1961, sufficiently proving the Tilt Prop concept to the extent necessary to proceed with what would become the X-19.

In 1969, Curtiss-Wright donated the X-100 to the Smithsonian Institution, as an example of VTOL technology.

Source: AHS V/STOL Wheel

Overview

Data on design, manufacture and status

Design authority: Curtiss-Wright Corporation

Primary manufacturer: Curtiss-Wright Corporation

Parent type: No type defined

Aircraft status: No longer flying

Configuration

Primary flight and mechanical characteristics

VTOL type: Convertiplane

Compound type: N/A

Lift configuration: Tilt shaft (x2)

Dedicated control device: Other

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:  
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

Weights
Max Gross Weight (ground): 1,588 kg 3,500 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 1,588 kg 3,500 lb
Empty Weight:  
Useful Load:  
Empty Weight Fraction:  
Climb Performance
Max Rate of Climb:  
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Limitations
Max Level Flight Speed:  
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.

Powerplant
Number of engines: 1
Designation: Lycoming YT53-L-1 turbine
Manufacturer: Lycoming Engines
Normal Ratings
Max continuous:  
Take-off / rated: 642 kW 860 hp
Intermediate:  
Maximum:  
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:  
RPM:  
Direction of Rotation: Unknown
Hub Type:  
Main Rotor Blade Characteristics
Blade Construction:  
Blade Chord:  
Blade Tip Geometry:  
Blade Twist:  
Number of Blades:  
Main Rotor Derived Characteristics
Disc Area:  
Disc Loading:  
Solidity:  
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
Diameter:  
Configuration: Unknown
Direction of Rotation: Unknown
RPM:  
Tail Rotor Blade Characteristics
Number of Blades:  
Blade Construction: N/A
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area:  
Solidity:  
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade):  

Related VFS Resources

Resources related to the X-100 , provided by the Vertical Flight Society.
Forum Proceedings
 
Vertiflite articles
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Web files from vtol.org
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Webpages from vtol.org
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Related Public Resources

Resources related to the X-100 , provided by public sources across the internet.

Images