SNCAC NC 211

NC 211 Cormoran

First and only production NC-211
Role	Civil/Passenger
National origin	France
Manufacturer	SNCAC (Société Nationale de Constructions Aéronautiques du Centre) / (Aérocentre)
First flight	20 July 1948^[1]
Number built	2 + 9 partially completed^[1]

The SNCAC NC.211 Cormoran was a large four-engined military transport aircraft for passengers and cargo designed and built by SNCAC from 1945.

Design and development

in 1945, the French military wanted to create paratrooper divisions, but quickly found that they did not have any aircraft that could be used for this purpose. So, General Juin, the then chief of staff, ordered the Direction Technique Industrielle to evaluate the interest for this project. SNCAC and Breguet Aviation answered positively and the SNCAC NC.210 was selected in December 1945 when a contract for 105 aircraft was awarded to SNCAC.^[1]

The NC.211 originated as the NC.210 powered by four 1,641 kW (2,200 hp)^[2] Gnome-Rhône 18R 18-cylinder radial engines. With a change of engine type to the 1,193 kW (1,600 hp) Gnome-Rhône 14R the designation changed to NC.211. Intended to provide the French Air Force, (French: Armée de l'Air (ALA), literally Army of the Air), with strategic transport and paratrooping capability the Cormoran was a large four-engined aircraft with a double-deck fuselage, high-set wing and tricycle undercarriage. Constructed largely of light-alloys with stressed skins and steel high stress components the Cormoran had a conventional tail unit with tailplane attached to the extreme rear of the fuselage and fin also. The cockpit was situated forward of the wing leading edge above the forward fuselage which also had large clamshell doors to the 150 m³ (5,297 cu ft) lower deck cargo compartment. Passengers, paratroops and stretchers were to have been carried in both the lower cabin and the upper cabin, which was on the same level as the cockpit aft of the wing. The retractable twin-wheeled undercarriage legs retracted into the rear of the inboard engine nacelles and the underside of the forward fuselage.^[1]

History

After the fuselage of the first prototype was displayed at the 1946 Salon dÁeronautique in Paris on November 15, 1946 the first flight was delayed due to hydraulic problems on the landing gear. The first prototype Nc.211-01 was ready to fly in July 1948 making its first and only flight on 20 July 1948 at Toussous. During the flight a mis-match between flaps and tailplane/elevators caused the crash of the aircraft with the loss of all five on board.^[1]

Flight testing of the first production aircraft, from 9 April 1949, quickly revealed less than sparkling performance, leading to loss of confidence in the aircraft's ability to fulfil the requirement, (and possibly the safety of the design), resulting in cuts to the contract to ten production airframes. Flying with this aircraft ceased on 7 July 1949 with approximately 30 hours total flying time, after which the aircraft was used to house radio transmitters on the airfield at Villacoublay until it was scrapped circa 1972/3. All remaining aircraft and components were scrapped at the Aérocentre factory at Bourges or at Billancourt airfield.^[1]

Variants

Data from:^[1]

NC.210: The initial design powered by 4x 1,641 kW (2,200 hp) Gnome-Rhône 18R 18-cylinder radial engines. Not built.
NC.211: The proposed production aircraft powered by 4x 1,193 kW (1,600 hp) SNECMA 14R 14-cylinder radial engines. One prototype and one production aircraft completed with nine more partially completed.
NC.212: A proposed version to have been powered by 4x 1,476 kW (1,980 hp) Bristol Hercules 730 14-cylinder sleeve-valve radial engines.
NC.213: A proposed version to have been powered by 4x 1,305 kW (1,750 hp) Junkers Jumo 213 inverted V-12 engines.

Specifications (NC.211)

Data from French Postwar Transport Aircraft^[1]

General characteristics

Crew: 5
Capacity: 12,000 kg (26,455 lb) payload, 76 paratroops, 60 stretchers or 100-150 passengers (civil)
Length: 30.5 m (100 ft 1 in)
Wingspan: 44 m (144 ft 4 in)
Height: 10.7 m (35 ft 1 in)
Wing area: 200 m² (2,200 sq ft)
Empty weight: 25,625 kg (56,493 lb)
Gross weight: 42,250 kg (93,145 lb)
Powerplant: 4 × SNECMA 14R 14-cyl. two-row air-cooled radial piston engines, 1,200 kW (1,600 hp) each at 2,600 rpm with 47.2 in (1,199 mm) Hg / +8.6 psi (59,295 Pa) boost for take-off
Propellers: 3-bladed, 4 m (13 ft 1 in) diameter

Performance

Maximum speed: 390 km/h (242 mph; 211 kn) at 3,000 m (9,843 ft)
Cruising speed: 288 km/h (179 mph; 156 kn) at 3,000 m (9,843 ft)
Range: 1,000 km (621 mi; 540 nmi) with full payload
Range with 9,600 kg (21,164 lb) payload: 2,000 km (1,243 mi; 1,080 nmi)
Service ceiling: 8,000 m (26,247 ft)
Wing loading: 210 kg/m² (43 lb/sq ft)
Power/mass: 0.0284 kW/kg (0.0369 hp/lb)

Notes

1 2 3 4 5 6 7 8 Chillon, J.; J.P Dubois; J. Wegg (1980). French Postwar Transport Aircraft. Tonbridge: Air Britain. pp. 157–158. ISBN 0 85130 078 2.
↑ Wilkinson, Paul H. (1945). Aircraft Engines of the World 1945. New York: Paul H. Wilkinson.

References

Wikimedia Commons has media related to SNCAC.

Wilkinson, Paul H. (1945). Aircraft Engines of the World 1945. New York: Paul H. Wilkinson.
EADS: History of aviation > SNCAC NC211-Cormoran
Sandras-Dextreit, Geneviève. "L'Histoire du Cormoran". Bulletin Groupe Historique de Toussus-le-Noble, No. 6, 2001. Retrieved 29 December 2012.

Aircraft produced by the Société Nationale de Constructions Aéronautiques du Centre (SNCAC)

NC.130 NC.150 NC.223 NC.4-10 NC.420 NC.433 NC.47-0 NC.47-1 NC.47-2 NC.510 NC.530 NC.600 NC.700 NC.701 NC.702 NC.832 NC.840 NC.841 NC.850 NC.851 NC.853 NC.854 NC.855 NC.856 NC.860 NC.900 NC.1070 NC.1071 NC.1080 NC.2001 NC.211 NC.271 NC.3021

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