First helicopter of Landgraf Helicopter Corporation developed in 1944.  Bought by the USAF for testing in 1948; however, the aircraft crashed in the testing and the pilot was killed.  The project was halted following the incident.

For further details on the design and development history of the aircraft see,

Source: “Landgraf Helicopter Co. Model H-2 Lateral-Twin Helicopter”, Ken Bartie, VFS 2019 VTOL History Calendar


Data on design, manufacture and status

Design authority: Landgraf Helicopter Corporation

Primary manufacturer: Landgraf Helicopter Corporation

Parent type: No type defined

Aircraft status: No longer flying


Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Tandem (Lateral) (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: 4.57 m 15.0 ft
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

Cruise Speed: 70 mph (112.654 km/h)

Max Gross Weight (ground): 386 kg 850 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 386 kg 850 lb
Empty Weight: 288 kg 636 lb
Useful Load: 97 kg 214 lb
Empty Weight Fraction: 0.748
Climb Performance
Max Rate of Climb:  
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Max Level Flight Speed: 137 km/h 74 kts
Never Exceed Speed:  
Service Ceiling:  
Range and Endurance
Max Range: 187 km 101 nm
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: Pobjoy R reciprocating
Manufacturer: Pobjoy Airmotors Limited
Normal Ratings
Max continuous:  
Take-off / rated: 63 kW 85 hp
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

The rotors were inter-meshing. Blade tip mounted ailerons provided directional control. The rotor hubs were re-designed in steel following the a crash caused by a failure of one of the wodden hubs.

Main Rotor Characteristics
Diameter: 4.88 m 16.00 ft
Direction of Rotation: Counter-rotating
Hub Type:
Main Rotor Blade Characteristics
Blade Construction: Solid Wood
Blade Chord:  
Blade Tip Geometry: Elliptic
Blade Twist:  
Number of Blades: 3
Main Rotor Derived Characteristics
Disc Area: 18.68 m² 201.1 ft²
Disc Loading: 10.32 kg/m² 2.114 lb/ft²
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):  

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