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Lockheed XH-51 (A) helicopter

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Specifications Comment this helicopter
Picture XH-51(A)
General
Manufacturer Lockheed
Type XH-51 (A)
Introduced 11/2/1962
In production? No
Units produced 3
Price US $ 0.00
Dimensions
Overall Length 40.7 ft
Length 31.8 ft
Height 8.2 ft
Width 0 ft
   
   
Description

The XH-51A Model (186) was an experimental helicopter made by Lockheed Aircraft. It first took flight in 1962.

The XH-51 was a specialised test-bed for technologies developed in joint research between the US Army and Navy.

It was a three-bladed, single-engine helicopter that made use of a rigid rotor. The skid landing gear was retractable.

The joint research program ordered two XH-51As. These had four seats and were powered by a 550 shaft horsepower Pratt & Whitney PT6B-9 turboshaft engine.

During initial flight testing it became apparent that the rigid bladed were not very good at higher speeds, becoming unstable. So the XH-51 was refitted with a four-bladed rotor.

One of the XH-51A helicopters was modified in a compound helicopter, adding an additional source of thrust. As such it was equipped with wings and a 2500 horsepower Pratt & Whitney J60-2 turbojet.

Using this setup the XH-51 compound version reached a speed of 413 kilometers per hour or about 257 miles per hour.

Two demonstrator craft were built, designated Model 286. They had five seats and carried over the four-bladed rotor from the Model 186.

Lockheed never sold any Model 286- or 186- derived units and only three X-51 craft were ever built.

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Design features
  • Retractable skid type landing gear
  • Aluminum, flush-sealed fuselage
  • Covered swash plate
  • Control rods run through main rotor shaft
Description

The XH-51A Model (186) was an experimental helicopter made by Lockheed Aircraft. It first took flight in 1962.

The XH-51 was a specialised test-bed for technologies developed in joint research between the US Army and Navy.

It was a three-bladed, single-engine helicopter that made use of a rigid rotor. The skid landing gear was retractable.

The joint research program ordered two XH-51As. These had four seats and were powered by a 550 shaft horsepower Pratt & Whitney PT6B-9 turboshaft engine.

During initial flight testing it became apparent that the rigid bladed were not very good at higher speeds, becoming unstable. So the XH-51 was refitted with a four-bladed rotor.

One of the XH-51A helicopters was modified in a compound helicopter, adding an additional source of thrust. As such it was equipped with wings and a 2500 horsepower Pratt & Whitney J60-2 turbojet.

Using this setup the XH-51 compound version reached a speed of 413 kilometers per hour or about 257 miles per hour.

Two demonstrator craft were built, designated Model 286. They had five seats and carried over the four-bladed rotor from the Model 186.

Lockheed never sold any Model 286- or 186- derived units and only three X-51 craft were ever built.

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Design features:
  • Retractable skid type landing gear
  • Aluminum, flush-sealed fuselage
  • Covered swash plate
  • Control rods run through main rotor shaft
Performance
Persons 4
Max. Range 260 mi
Cruise Speed 160 mph
Max. Speed 174 mph
Max. rate of Climb 2000 ft/min
HOGE ceiling 0 ft
Service Ceiling 16000 ft
Gross Weight 4100 lb
Empty Weigt 2790 lb
Useful Load 1310 lb
Dynamic system
Fuel Capacity 0 gallons
Number of Engines 1
Engine Type Turbine
Engine Code Pratt & Whitney Canada PT6B-9
Horse Power 550
Rotorhead Rigid
Number of rotorblades 3
Rotor Diameter 35 ft
Number of tail rotorblades 2
Tailrotor Diameter 0 ft
Blueprints & model
Manufacturer Website manufacturer..
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