C-124 Globemaster II

In 1947, when the newly organized U.S. Air Force (USAF) formulated requirements for a strategic transport aircraft, negotiations were held with the Douglas firm. As a result, a suitable aircraft, designated C-124 Globemaster II, was developed based on the C-74. Its prototype, the YC-124, was effectively the fifth production C-74 with a new, taller fuselage, strengthened landing gear, and a power plant of four R-4360-49 engines, each rated at 3,500 hp (2,610 kW).

The YC-124’s first flight took place on November 27, 1949. After completing its trials, the aircraft entered series production as the C-124A, with a total of 204 machines built. The first of these was delivered to the USAF in May 1950.

Cargo Capabilities and Crew

The next and final production variant was the C-124C, equipped with more powerful R-4360 engines, a weather radar in its distinctive fairing, and anti-icing system heaters in the wingtips. 243 C-124C examples were built, with the last being delivered to the customer in May 1955.

The Globemaster II’s fuselage featured a bi-fold nose cargo door with an integrated loading ramp. It also incorporated electric winches in the mid-fuselage section and two overhead bridge cranes (each with a lifting capacity of 7,257 kg and capable of moving along the entire 23.47 m length of the cargo bay). The cockpit, designed for a five-person crew, was located at the top of the aircraft’s nose section.

When used as a transport aircraft (with two cargo decks), the Globemaster II could carry 200 fully equipped soldiers. Alternatively, it was capable of transporting 123 stretchers plus 45 ambulatory patients and 15 medical personnel. This versatility made it a crucial asset for logistical and humanitarian operations.

Special Projects and Legacy

One C-124C was converted into a flying testbed, designated JC-124C, and used to test the Pratt & Whitney XT57 engine (15,000 hp). This engine was intended for the projected Douglas C-132 aircraft, which aimed for a cargo capacity of over 60 tons. However, during testing, the engine demonstrated numerous technical problems, leading to the program’s cancellation in 1957.

Alongside the C-133 aircraft, the Globemaster II remained in service with various USAF air commands until the 1970s. They were eventually replaced by the C-5A, marking the end of an era for this robust strategic transport. Its legacy, however, remains significant in military aviation history.

Technical Specifications

Modification	S-124S
Wingspan, m	53.1
Aircraft length, m	39.8
Aircraft height, m	14.7
Wing area, m2	233.1
Empty weight	45888
Normal takeoff weight	84000
Maximum takeoff weight	88200
Engine type	4 Piston engines Pratt Whitney R-4360-63
Power, hp	4 x 3748
Maximum speed, km/h	520
Cruising speed, km/h	429
Practical range, km	11000
Operational range, km	6500
Service ceiling, m	8000
Crew, crew members	8
Payload	200 soldiers or 127 stretchers with attendants or 31070 kg of cargo

Image and diagram gallery of the C-124 Globemaster II

C-124 Globemaster II	C-124 Globemaster II
C-124 Globemaster II	C-124 Globemaster II
C-124 Globemaster II	C-124 Globemaster II
C-124 Globemaster II	C-124 Globemaster II
C-124 Globemaster II	C-124 Globemaster II
C-124 Globemaster II	C-124 Globemaster II
C-124 Globemaster II	C-124 Globemaster II