The Vertol 76 received the Army designation VZ-2 in early 1956. The 26.5 ft fuselage was built of metal tube construction, and had a helicopter-like two seat cockpit. A single 860 bhp Lycoming YT53-L-1 was mounted on the fuselage, and drove the two 9.5 ft three-bladed propellers by a cross-shaft through the 25 ft span wings. In hover, pitch and yaw were controlled by two ducted propellers in the tail; in transition, aerodynamic controls were phased in until the tail propellers were no longer needed in horizontal flight.

Ground testing began in April 1957. The first vertical flight was made on 13 August 1957, first horizontal flight on 7 January 1958, and first complete transition on 15 July 1958. It continued to fly until 1965, making over 450 flights, including 34 full conversions.

Source: AHS V/STOL Wheel

Overview

Data on design, manufacture and status

Design authority: Vertol Aircraft Corporation

Primary manufacturer: Vertol Aircraft 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 wing (x2)

Dedicated control device: Fenestron/Shrouded tail rotor (x2)

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):  
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:  
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
Normal Ratings
Max continuous:  
Take-off / rated:  
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 76/VZ-2 , 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 76/VZ-2 , provided by public sources across the internet.

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