Vertipedia - Sikorsky CH-37A/H-37A Mojave

Utility transport version for the US Army. The aircraft was re-designated to CH-37A in 1962 as part of the overall rationalization of designations for US Armed Forces aircraft.

The aircraft included a manually folded main rotor and hydraulically folded tail rotor pylon.

Source: S-56/HR2S-1/H-37 Helicopter, Vinny Devine, Igor I. Sikorsky Archives, April 2013)

Overview

Data on design, manufacture and status

Design authority: Sikorsky Aircraft Division, United Aircraft and Transport Corporation

Primary manufacturer: Sikorsky Aircraft Division, United Aircraft and Transport Corporation

Parent type: Sikorsky S-56/H-37

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: 2 in Side-by-side arrangement

Landing gear: Wheels (all 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:

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:

Weights
Max Gross Weight (ground):
Max Gross Weight (airborne):
Max Take-off Weight:
Empty Weight:
Useful Load:
Empty Weight Fraction:

Climb Performance
Max Rate of Climb:

Hover Performance
Hover Ceiling IGE:
Hover Ceiling OGE:

Limitations
Max Level Flight Speed:
Never Exceed Speed:
Service Ceiling:

Range and Endurance
Max Range:
Max Endurance:

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

Powerplant
Number of engines:	2

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

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

Originally fitted with blades using the NACA 0012 airfoil, higher-performing wide-chord blades using the NACA 0010.9 airfoil were retrofitted across all models.

Main Rotor Characteristics
Diameter:	21.95 m	72.00 ft
RPM:	184.0 rpm	184.0 rpm
Direction of Rotation:	Unknown
Hub Type:	Fully articulated main rotor head with a 24-inch offset flapping hinge

Main Rotor Blade Characteristics
Blade Construction:	Hollow extruded aluminum spar with 27 honeycomb filled, aluminum skinned pockets bonded to the spar, with steel cuffs.
Blade Chord:	0.601 m	1.97 ft
Blade Tip Geometry:	Square tips
Blade Twist:	-0.140 rad	-8.000 deg
Number of Blades:	5

Main Rotor Derived Characteristics
Disc Area:	378.25 m²	4071.6 ft²
Disc Loading:
Solidity:	0.0871

Main Rotor Blade Derived Characteristics
Blade area per blade:	6.59 m²	71.0 ft²
Tip Speed:	211.43 m/s	693.7 fps

Tail Rotor Characteristics
Diameter:	4.57 m	15.00 ft
Configuration:	Pusher
Direction of Rotation:	Top blade fwd
RPM:

Tail Rotor Blade Characteristics
Number of Blades:	4
Blade Construction:	All metal (aluminum)
Blade Chord:	0.343 m	1.13 ft
Blade Twist:	-0.17 rad	-10.0 deg

Tail Rotor Derived Characteristics
Disc Area:	16.42 m²	176.7 ft²
Solidity:	0.1910

Tail Rotor Blade Derived Characteristics
Tip Speed:
Blade Area (per blade):	0.784 m²	8.44 ft²

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Images

Tail rotor

Attribution

Main Rotor Diameter:	21.95 m	72.00 ft
Max Gross Weight (ground):
Useful Load (calculated):

Number of engines:	2 Unknowns
Max Level Flight Speed:
Max Range:
Max Endurance: