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)

Overall Dimensions

Data on aircraft size

Engine Details

Aircraft powerplant (lift and/or propulsion)

Total number of engines: 1

Weights and Performance

Data on aircraft weight and flight characteristics

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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Related Public Resources

Resources related to the 76/VZ-2 , provided by public sources across the internet.

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