The H-21A is the general purpose version of the H-21 series, used in the U.S. Air Force.  Ten to sixteen passengers can be accommodated.

Overview

Data on design, manufacture and status

Design authority: Piasecki Helicopter Corporation

Primary manufacturer: Piasecki Helicopter Corporation

Parent type: Piasecki H-21

Aircraft status: No longer flying

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Tandem (Fore/aft) (x2)

Crew required: 2

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Overall Dimensions

Data on aircraft size

Overall Height: 4.69 m (15.4 ft)

Overall Length: 26.31 m (86.3 ft)

Overall Width: 13.41 m (44.0 ft)

Engine Details

Aircraft powerplant (lift and/or propulsion)

Total number of engines: 1

Engine designation: Wright R-1820-103 (derated) reciprocating

Engine manufacturer: Wright Aeronautical Division, Curtiss-Wright Corporation

Max continuous power: 858 kW (1150 hp)

Take-off / rated power: 858 kW (1150 hp)

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground): 5200 kg (11464 lb)

Max Range: 805 km (434 nm)

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