McDonnell Model 120 Flying Crane
Developed in 1958, the helicopter is powered by three turbo-compressors; the tip-jet aircraft can operate on two of its three engines, which can function independently. The XV-1 Convertiplane rotor was used for the Model 120. To steer, the engine exhaust was used [Ref Hirschberg. The American Helicopter. Page 62].
Overview
Data on design, manufacture and statusDesign authority: McDonnell Aircraft Corporation
Primary manufacturer: McDonnell Aircraft Corporation
Parent type: No type defined
Aircraft status: No longer flying
Configuration
Primary flight and mechanical characteristicsVTOL type: Helicopter
Lift configuration: Single main rotor
Crew required: 1
Crew seating: Single seater
Landing gear: Skids
Layout and Dimensions
Data on aircraft size| Overall Dimensions | ||
|---|---|---|
| Overall Height: | 2.74 m | 9.0 ft |
| Overall Length: | 9.45 m | 31.0 ft |
| Overall Width: | 9.45 m | 31.0 ft |
| Airframe Dimensions | ||
|---|---|---|
| Airframe Length: | 6.10 m | 20.0 ft |
| Airframe Width: | ||
| Airframe Height: | 2.74 m | 9.0 ft |
| Landing Gear Dimensions | ||
|---|---|---|
| Landing Gear Base: | ||
| Landing Gear Track: | 2.79 m | 9.2 ft |
| Cabin Dimensions | ||
|---|---|---|
| Cabin Internal Height: | ||
| Cabin Internal Length: | ||
| Cabin Internal Width: | ||
Weights and Performance
Data on aircraft weight and flight characteristicsCruise Speed: 109 mph (175 km/h)
| Weights | ||
|---|---|---|
| Max Gross Weight (ground): | 2,858 kg | 6,300 lb |
| Max Gross Weight (airborne): | ||
| Max Take-off Weight: | 2,858 kg | 6,300 lb |
| Empty Weight: | 1,111 kg | 2,450 lb |
| Useful Load: | 1,746 kg | 3,850 lb |
| Empty Weight Fraction: | 0.389 | |
| Climb Performance | ||
|---|---|---|
| Max Rate of Climb: | 12 m/s | 2,400 fpm |
| Hover Performance | ||
|---|---|---|
| Hover Ceiling IGE: | 3,658 m | 12,001 ft |
| Hover Ceiling OGE: | 3,048 m | 10,000 ft |
| Limitations | ||
|---|---|---|
| Max Level Flight Speed: | 222 km/h | 120 kts |
| Never Exceed Speed: | ||
| Service Ceiling: | ||
| Range and Endurance | ||
|---|---|---|
| Max Range: | 158 km | 85 nm |
| Max Endurance: | 1 hrs | 1 hrs |
Engine Details
Aircraft powerplant (lift and/or propulsion)Provided powerplant data is for uninstalled, sea level, static operations.
| Powerplant | ||
|---|---|---|
| Number of engines: | 3 | |
| Designation: | AiResearch GTC-85-35 turbine | |
| Manufacturer: | AiResearch | |
| Normal Ratings | ||
|---|---|---|
| Max continuous: | ||
| Take-off / rated: | 63 kW | 85 hp |
| 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: | 9.45 m | 31.00 ft |
| RPM: | 410.0 rpm | 410.0 rpm |
| Direction of Rotation: | Clockwise | |
| Hub Type: | Stiff inplane, bearingless, damperless | |
| Main Rotor Blade Characteristics | ||
|---|---|---|
| Blade Construction: | ||
| Blade Chord: | ||
| Blade Tip Geometry: | Swept Tip-jet | |
| Blade Twist: | ||
| Number of Blades: | 3 | |
| Main Rotor Derived Characteristics | ||
|---|---|---|
| Disc Area: | 70.14 m² | 755.0 ft² |
| Disc Loading: | 40.74 kg/m² | 8.345 lb/ft² |
| Solidity: | ||
| Main Rotor Blade Derived Characteristics | ||
|---|---|---|
| Blade area per blade: | ||
| Tip Speed: | 202.87 m/s | 665.6 fps |
Primary Control Device
Data on primary control devices such as tail rotors| Tail Rotor Characteristics | ||
|---|---|---|
| Diameter: | ||
| Configuration: | Unknown | |
| Direction of Rotation: | Unknown | |
| RPM: | ||
| Tail Rotor Blade Characteristics | ||
|---|---|---|
| Number of Blades: | ||
| Blade Construction: | N/A | |
| Blade Chord: | ||
| Blade Twist: | ||
| Tail Rotor Derived Characteristics | ||
|---|---|---|
| Disc Area: | ||
| Solidity: | ||
| Tail Rotor Blade Derived Characteristics | ||
|---|---|---|
| Tip Speed: | ||
| Blade Area (per blade): | ||
