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 statusDesign authority: Doman Helicopters Inc.
Primary manufacturer: Doman Helicopters Inc.
Parent type: No type defined
Aircraft status: No longer flying
Configuration
Primary flight and mechanical characteristicsVTOL type: Helicopter
Lift configuration: Single main rotor
Dedicated control device: Tail rotor
Crew required: 1
Crew seating: Side-by-side
Landing gear: Wheels (non-retractable)
Layout and Dimensions
Data on aircraft size| 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: | ||
Weights and Performance
Data on aircraft weight and flight characteristicsCruise 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: | ||
Engine Details
Aircraft powerplant (lift and/or propulsion)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: | ||
Primary Lift Device
Data on primary lift devices such as main rotors| 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: | ||
Primary Control Device
Data on primary control devices such as tail rotors| 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): | ||
