Vertipedia - Bell UH-1A Iroquois

A 6-place helicopter derived from the XH-40 in 1960 for the US Army. Used in Vietnam during the war beginning in Fall 1962 [AHS History Calendar | October 2017].

Overview

Data on design, manufacture and status

Latest or last design authority: Bell Helicopter Company
Originally designed by Bell Helicopter Corporation

Latest or last primary manufacturer: Bell Helicopter Company
Originally manufactured by Bell Helicopter Corporation

Parent type: Bell Model 204/UH-1 Iroquois

Aircraft status: Status unknown

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift devices: 1 Single main rotor

Dedicated control device: 1 Tail rotor

Crew required: 2 in Side-by-side arrangement

Landing gear: Skids

Key Characteristics

Data on key physical features

Aircraft Details

Data on aircraft configuration, weights, flight performance and equipment

Layout and Dimensions

Weights and Performance

Engine Details

Primary Lift Device

Primary Control Device

Overall Dimensions
Overall Height:
Overall Length:
Overall Width:	13.41 m	44.0 ft

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:

Cruise Speed: 115 mph (185.075 km/h)

Weights
Max Gross Weight (ground):	3,266 kg	7,200 lb
Max Gross Weight (airborne):
Max Take-off Weight:	3,266 kg	7,200 lb
Empty Weight:
Useful Load:
Empty Weight Fraction:

Climb Performance
Max Rate of Climb:	11 m/s	2,100 fpm

Hover Performance
Hover Ceiling IGE:
Hover Ceiling OGE:	3,505 m	11,500 ft

Limitations
Max Level Flight Speed:	227 km/h	123 kts
Never Exceed Speed:
Service Ceiling:

Range and Endurance
Max Range:	338 km	182 nm
Max Endurance:

Provided powerplant data is for uninstalled, sea level, static operations.

Powerplant
Number of engines:	1
Designation:	Lycoming T53-L-1A turbine
Manufacturer:	Lycoming Engines

Normal Ratings
Max continuous:	567 kW	760 hp
Take-off / rated:	633 kW	848 hp
Intermediate:
Maximum:

OEI Ratings
OEI contingency:
OEI continuous:
OEI 30-second:
OEI intermediate:

Main Rotor Characteristics
Diameter:	13.41 m	44.00 ft
RPM:
Direction of Rotation:	Counterclockwise
Hub Type:	Semi-rigid

Main Rotor Blade Characteristics
Blade Construction:	All-metal
Blade Chord:	0.381 m	1.25 ft
Blade Tip Geometry:
Blade Twist:
Number of Blades:	2

Main Rotor Derived Characteristics
Disc Area:	141.26 m²	1520.6 ft²
Disc Loading:	23.12 kg/m²	4.735 lb/ft²
Solidity:	0.0362

Main Rotor Blade Derived Characteristics
Blade area per blade:	2.55 m²	27.5 ft²
Tip Speed:

Tail Rotor Characteristics
Diameter:	2.59 m	8.50 ft
Configuration:	Pusher
Direction of Rotation:	Top blade fwd
RPM:

Tail Rotor Blade Characteristics
Number of Blades:	2
Blade Construction:
Blade Chord:
Blade Twist:

Tail Rotor Derived Characteristics
Disc Area:	5.27 m²	56.7 ft²
Solidity:

Tail Rotor Blade Derived Characteristics
Tip Speed:
Blade Area (per blade):

References

References and sources used

Helicopters from "A to Z" | Part I

Ralph P. Alex
AHS Newsletter, 1961, October, 1961 (page 9)
Periodical

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Images

Overview

Attribution

Number of engines:	1 Turbine
Max Level Flight Speed:	227 km/h	123 kts
Max Range:	338 km	182 nm
Max Endurance:

Main Rotor Diameter:	13.41 m	44.00 ft
Max Gross Weight (ground):	3,266 kg	7,200 lb
Useful Load (calculated):