The Ryan 92, designated VZ-3 by the Army in June 1956, was intended to be a reconnaissance and liaison aircraft able to operate from unprepared surfaces. It had a 28 ft metal fuselage and was powered by a 1,000 shp Lycoming T53-L-1 turboshaft engine driving a metal three-blade Harzell propeller on each side. The propellers were situated ahead of and below the wing, so the majority of the propeller slipstream flowed directly into the bucket formed by the extended double flaps and were turned downward for vertical lift. Differential propeller pitch was used for roll control. Engine exhaust was used at the tail for pitch and yaw before aerodynamic controls were effective. Ryan began taxiing trials on 7 February 1958.

After extensive wind tunnel tests and aircraft modifications the first flight was made on 21 January 1959. The engines were unable to provide sufficient power to hover without a head wind. An accident the next month grounded it for repairs until its first test by NASA in February 1960; unfortunately the pilot ejected after an unplanned maneuver. It was again rebuilt to flying status: modifications after the crash led to a fabric nose section, an open cockpit, and a different landing gear. It continued flying in 1961, testing low-speed V/STOL handling characteristics.

Source: AHS V/STOL Wheel


Data on design, manufacture and status

Design authority: Ryan Aeronautical

Primary manufacturer: Ryan Aeronautical

Parent type: No type defined

Aircraft status: No longer flying


Primary flight and mechanical characteristics

VTOL type: Other

Compound type: N/A

Lift configuration: Deflected slipstream (x2)

Dedicated control device: Other (x4)

Crew required: 1

Crew seating: Single seater

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

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:  
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: 1
Designation: Lycoming T53-L-1 turbine
Manufacturer: Lycoming Engines
Normal Ratings
Max continuous:  
Take-off / rated: 641 kW 860 hp
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
Direction of Rotation: Not applicable
Hub Type:
Main Rotor Blade Characteristics
Blade Construction:
Blade Chord:  
Blade Tip Geometry:
Blade Twist:  
Number of Blades: 3
Main Rotor Derived Characteristics
Disc Area:  
Disc Loading:  
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):  

Related VFS Resources

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Related Public Resources

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