Vertipedia - Doman LZ-4 (CW-40)

The aircraft was built by Doman and later financed by Curiss Wright (as a development vehicle). The aircraft was designated as the CW-40 by Curtiss Wright.

The aircraft was an 8 place machine.

Tthe aircraft also served as the prototype fro the LZ-5 (YH-31).

Overview

Data on design, manufacture and status

Design authority: Doman Helicopters Inc.

Primary manufacturer: Doman Helicopters Inc.

Parent type: No type defined

Aircraft status: No longer flying

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift devices: 1 Single main rotor

Dedicated control device: 1 Tail rotor

Crew required: 1 in Side-by-side arrangement

Landing gear: Wheels (non-retractable)

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:	14.63 m	48.0 ft

Airframe Dimensions
Airframe Length:	11.61 m	38.1 ft
Airframe Width:
Airframe Height:	3.40 m	11.2 ft

Landing Gear Dimensions
Landing Gear Base:
Landing Gear Track:

Cabin Dimensions
Cabin Internal Height:
Cabin Internal Length:
Cabin Internal Width:

Cruise Speed: 78 mph (126 km/h)

Weights
Max Gross Weight (ground):	2,132 kg	4,700 lb
Max Gross Weight (airborne):
Max Take-off Weight:	2,132 kg	4,700 lb
Empty Weight:	1,347 kg	2,970 lb
Useful Load:	785 kg	1,730 lb
Empty Weight Fraction:	0.632

Climb Performance
Max Rate of Climb:	4 m/s	800 fpm

Hover Performance
Hover Ceiling IGE:
Hover Ceiling OGE:

Limitations
Max Level Flight Speed:
Never Exceed Speed:
Service Ceiling:	4,877 m	16,000 ft

Range and Endurance
Max Range:	338 km	183 nm
Max Endurance:

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

Powerplant
Number of engines:	1
Designation:	Lycoming SO-590-B reciprocating
Manufacturer:	Lycoming Engines

Normal Ratings
Max continuous:
Take-off / rated:
Intermediate:
Maximum:

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

Main Rotor Characteristics
Diameter:	14.63 m	48.00 ft
RPM:
Direction of Rotation:	Clockwise
Hub Type:

Main Rotor Blade Characteristics
Blade Construction:
Blade Chord:
Blade Tip Geometry:
Blade Twist:
Number of Blades:	4

Main Rotor Derived Characteristics
Disc Area:	168.11 m²	1809.6 ft²
Disc Loading:	12.68 kg/m²	2.597 lb/ft²
Solidity:

Main Rotor Blade Derived Characteristics
Blade area per blade:
Tip Speed:

Tail Rotor Characteristics
Diameter:
Configuration:	Tractor
Direction of Rotation:	Unknown
RPM:

Tail Rotor Blade Characteristics
Number of Blades:	3
Blade Construction:
Blade Chord:
Blade Twist:

Tail Rotor Derived Characteristics
Disc Area:
Solidity:

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

References

References and sources used

Helicopters & Autogyros of the World

Paul Lambermont, Anthony Pirie
Cassell & Company Ltd., 1959 (page 263)
Book

Helicopters From "A to Z" | Part II

Ralph P. Alex
AHS Newsletter - November, 1961, November 1961 (page 5)
Periodical

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Images

Overview

Attribution

Number of engines:	1 Reciprocating
Max Level Flight Speed:
Max Range:	338 km	183 nm
Max Endurance:

Main Rotor Diameter:	14.63 m	48.00 ft
Max Gross Weight (ground):	2,132 kg	4,700 lb
Useful Load (calculated):	785 kg	1,730 lb