Sud Aviation V/STOL Aircraft
Sud Aviation
Sud-Ouest Aviation, Sud-Est Aviation -> Sud Aviation (1957) -> Aérospatiale (1970)
Light ground assault helicopter.
- Power: single Astazou 14 turboshaft engine, which drove an axial compressor to power the rotor
- Rotor: 10 m diameter
- Maximum Speed: 370 km/h (200kt)
- Wing span: 3.5 m
- Length: ~6.2 m
- Height: ~2.5 m
- Empty Weight: 1080 kg
- Capacity: five seats
- 3-side-view
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| 30 passenger Rotojet |
Compound |
- Power: jet engine mounted on either side of the fuselage
- Maximum Speed: 465 km/h (250kt)
- Empty Weight: 7780 kg
- Flight weight: 12,000 kg
- Capacity: 30-36 seats
- 2-side-view
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| Extendable rotor concept |
Compound |
A concept with a triangular inner hub area with extendable rotors was also studied during this time.
For vertical flight operations, the rotor blades extended and rotated to produce lift.
Once the vehicle reached a high enough forward velocity for the wings to provide adequate lift, the rotor blades
would retract and forward flight would be provided by two jet engines.
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| 30 passenger Transporter |
Compound |
In September 1967, a large compound design, was announced, with jet engines at the wing/fuselage junctions.
It was expected to carry around 50 passengers for 80-300 nm (150-555 km) at 250 kt (460 km/hr).
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| 40 passenger Rotor airliner |
Compound |
In Summer 1969, several new concepts were released to the press.
The largest concept is shown in the picture with the rotor stowed for high speed flight and the rotor extended, as it is preparing for take-off.
- Rotor: two 2-bladed retractable rotors
- Design Speed: 750 km/h (405 kt)
- Range: 800 km (430 nm)
- Weight: 14.5 t (32,000 lb)
- Capacity: 40 passengers
- 2-side-view
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In October 1959, Sud Aviation proposed the SA X-600 project against the Mirage III V.
For the radar, it would have used a Cyrano II (like the Mirage III) or the Super NASARR (like the F-104).
Sud Aviation stated that it could fly in 1967 if it was launched in 1960.
Other design variations were also considered, including with six lift engines, as well as a cranked delta planform.
- Lift Power: four RB.162
- Lift Thrust: 2,200 kg (4,850 lb) each
- Cruise Power: one RB.153 or RB.168
- Cruise Thrust: 5,030 kg + 8,700 kg (11,089 lb + 19,180 lb)
- Maximum speed: 2 Mach
- Wing span: 7.2 m (23.6 ft)
- Wing Area: 40 m² (47.9 ft²)
- Length: 14.6 m (47.9 ft)
- Empty Weight: 4,575 kg (10,086 lb)
- Maximum VTO Weight: 8,870 kg (19,555 lb)
- 3-side-view
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Top
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A concept with a triangular inner hub area with extendable rotors was also studied during this time.
For vertical flight operations, the rotor blades extended and rotated to produce lift.
Once the vehicle reached a high enough forward velocity for the wings to provide adequate lift, the rotor blades
would retract and forward flight would be provided by two jet engines.
In September 1967, a large compound design, was announced, with jet engines at the wing/fuselage junctions.
It was expected to carry around 50 passengers for 80-300 nm (150-555 km) at 250 kt (460 km/hr).
In Summer 1969, several new concepts were released to the press.
The largest concept is shown in the picture with the rotor stowed for high speed flight and the rotor extended, as it is preparing for take-off.
