Nord Avatation V/STOL Aircraft
Société Nationale de Constructions Aéronautiques du Nord (SNCAN) or Nord Aviation (France)
SFECMAS (1953) -> Nord Aviation -> Aérospatiale (1970)
| pre Nord 500 Cadet designs |
Tilt Duct |
Designs started 1964
Studies eventually led to the basic arrangement shown in the right picture with two ducted propellers that could
tilt 90º for horizontal or vertical thrust. It was also part of a more general program to explore a full-scale
"top-fan" system of high static efficiency with variable expansion of the air flow through the duct.
Another early concept was a two-seat tandem vehicle with a much larger and higher wing, as well as a landing gear
that retracted into the horizontal tail surfaces, as shown in the picture. It was planned to use two Turboméca Astazou engines with 750 hp (560 kW) each.
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| post Nord 500 Cadet designs |
Tilt Duct |
"Stage 2" development testing was planned in 1969, using controlled and variable expansion of the air flow through
the ducts. The concept was calculated to be able to reach a maximum forward speed of 350 km/hr (190 kt), but
development was canceled without being tested further. A third, refined airframe was also under construction, with
hydraulic controls and the more powerful Allison 250-C20 engines, each with 370 shp (275 kW).
The planned operational Cadet.
- Power: two Oredon 111 turboshafts with 350 shp (260 kW) each
- Fuel consumption: 0.39 kg/km (1.6 lb/nm)
- Wing span: 5.7 m (18.7 ft)
- Overall Length: 7.1 m
- Height: 2.17 m
- Empty Weight: 1,000 kg (2,200 lb)
- Gross VTO Weight: 1,850 kg (4,080 lb)
- Maximum Take-off Weight:
- Capacity: 4 seats
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Nord 501
Attack Aircraft |
Tilt Duct |
In 1966/67, the Centre de Prospective et d'Evaluation du ministère des Armées requested Nord Aviation to study a
military version of the Nord 500 intended for missions such as attack and helicopter escort. Other missions considered
were escort, tactical support, heli-hunter and for anti-submarine warfare (ASW). A model of the two-seat Nord 501 in
Navy markings was delivered in December 1968 and displayed at the Paris Air Show in 1969.
An operational version was expected to take six years to develop. The design mission was a 500 km (270 nm) cruise,
hover for 15 minutes, and return without the payload.
- Power: Two Lycoming LTC4-B-11 (military designation T55-L-IIB) turboshaft engines with 2,100 hp (1,565 kW) each
- Duct: 1.34 m (4.4 ft) diameter
- Maximum Speed: 600 km/h (325 kt)
- Wing span: 4.50 m (14.8 ft)
- Length: 8 m (26 ft)
- Empty Weight: 2,100 kg (4,630 lb)
- Payload: 1,900 kg (4,190 lb)
- Maximum VTO Weight: 4,000 kg (8,820 lb)
- Endurance: 1 hr 20 min
- Capacity: 2 seats
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Differend vesions of the Estocade ("death-blow").
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Nord 501
Transport Aircraft |
Tilt Duct |
The Nord 501 transport (it is not clear why the 501 designation was used again) was a concept for a pressurized
transport for civil or military applications, based on the general Cadet layout.
- Power: Two 2650 hp (1,976 kW) Lycoming T55-L-7 turboshafts
- Maximum Speed: 607 km/h (328 kt)
- Wing span: 5.7 m (18.6 ft)
- Overall Length: 10.3 m (33.7 ft)
- Height: 3.9 m (12.7 ft)
- Capacity: 2 crewmen and 8 passengers
- Gross Weight: 4,625 kg (10,200 lb)
- Crew: 2
- Capacity: 8 passengers
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The Rocade ("bypass") had a rather flat "V"-tail configuration.
A prototype was under construction when the Nord ducted propeller aircraft program was terminated.
- Power: four 1,100 hp (820 kW) Turboméca Turmo-IIIC engines
- Propellers: counter-rotating ducted propellers
- Duct: 5.46 m (17.9 ft) outside diameter; 4.7 m (15.4 ft) inner diameter
- Cruise Speed: 540 km/hr (300 kt)
- Fuel consumption: 2.0 kg/km (8.2 lb/nm)
- Overall Wing span: 19.5 m (64 ft)
- Length: 18.4 m (60.3 ft)
- Overall Height: 6.9 m (22.6 ft) ducts horizontal; 6.0 m (19.7 ft) ducts vertical
- Empty Weight: 9,450 kg (20,800 lb)
- Maximum VTO Weight: 15,700 kg (34,650 lb)
- Capacity: 40 passenger
- 3-side-view
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The Helcade was planned in 1963.
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Proposed in January 1960.
The 4210 was a subsonic design using a Bristol BE 53/8 (derived from the engine for the British Hawker P.1127,
the forerunner to the Harrier), producing 8 t of static thrust. Incidentally, the basic concept of thrust vectoring
used on the BE 53 Pegasus engine had actually been proposed to Bristol by Frenchman Michel Wilbault.
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The Nord 4400 was designed in January 1960 for supersonic flight, using the BS 100 (the BE 53 derivative for the
proposed supersonic Hawker P.1154) to produce more than 16 t of thrust. This concept was proposed for the NBMR 3
competition. The concepts were abandoned in April or May 1960.
Nord negotiated with Hawker for a cooperative agreement in early 1960 on developing the P.1127 for this requirement,
but this solution was rejected by the armée de l'Air.
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