After World War II, the US Navy was looking for ways to improve ship defense by equipping merchant ships with vertical take-off aircraft. A 1950 design competition selected Convair (#24) and Lockheed to each build a single-seat tail sitting fighter aircraft. Each used the Allison YT40-A-14 engine (two coupled T38 power sections mounted side-by-side) driving two 16 ft counter-rotating three-bladed Curtiss-Wright propellers with electric pitch control. The engines produced 5,500 eshp with a 7,100 eshp take-off rating, resulting in over 10,000 lb of thrust. The 37 ft fuselage had mid-mounted 30 ft span wings. Control in hover was by the same large aerodynamic surfaces as in level flight, as each was bathed in propeller slipstream; the "X"-shaped tail arrangement minimized downwash masking. An erector trolley was used to stand the XFV-1 in the vertical position; the tips of each tail had a small castoring wheel.

The aircraft was fitted with a temporary conventional attitude landing gear and made its first horizontal flight in March 1954. A total of 27 conventional flights were made, with the first full transitions made above 1,000 ft that Fall. Control in hover was very weak, and the pilot had difficulty in determining sink, climb, and rotation from normal visual cues. No vertical take-offs or landings were ever attempted. As with the Convair XFY-1 Pogo, the engine and control systems were judged to be insufficient.

Source: AHS V/STOL Wheel


Data on design, manufacture and status

Design authority: Lockheed Aircraft Corporation

Primary manufacturer: Lockheed Aircraft Corporation

Parent type: Lockheed XFV

Aircraft status: No longer flying


Primary flight and mechanical characteristics

VTOL type: Convertiplane

Compound type: N/A

Lift configuration: Tail sitter (x2)

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: Allison YT40-A-14 turbine
Manufacturer: Allison Engine Company
Normal Ratings
Max continuous:  
Take-off / rated:  
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: 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:  
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

Resources related to the XFV-1 , provided by the Vertical Flight Society.
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Related Public Resources

Resources related to the XFV-1 , provided by public sources across the internet.