SIPA Antilope
Antilope | |
---|---|
The sole SIPA Antilope exhibited at the Paris Air Show at Le Bourget in 1965 | |
Role | 4/5 seat turboprop light aircraft |
National origin | France |
Manufacturer | SIPA
|
First flight | 7 November 1962 |
Status | stored in a private museum |
Number built | 1 |
The SIPA S.251 Antilope was a low-wing
Design and development
The Antilope was one of the first turboprop powered light aircraft. Apart from its engine, it was a conventional all-metal low-wing machine. The cantilever wing was built around two spars and was a semi-monocoque structure, carrying unslotted ailerons and electrically powered, single slot
It had an electrically actuated tricycle undercarriage, the main wheels retracting inwards into the wings. The cabin had seats for four or five, two at the front and a bench seat behind. In a proposed air ambulance configuration, the Antilope would have carried two stretchers and a medic. Access to the cabin was via a large rear hinged door on the starboard side.[1]
The Antilope was powered by a 665 hp (495 kW) Turbomeca Astazou X driving a 3-bladed propeller, on a long spinner, well ahead of the surrounding air intake.[1]
It first flew on 7 November 1962 and gained certification in April 1964. That autumn, P. Bonneau set six international Class C1c (1000 – 1750 kg) records with it, achieving for example a speed of 432.9 km/h (267 mph) over a 3 km course and reaching an altitude of 10,420 m (34,186 ft). Early in 1965 it flew with a four-bladed propeller and improved on one of its own records. A three-blade propeller was re-installed and the aircraft was exhibited at the 1965 Paris Air Show wearing registration F-BJSS. By mid 1966 development had been completed without a decision to commence production.[1] The production version would have been known as the SIPA S.2510 Antilope but none were built; the prototype (F-WJSS) carried the designation S.251 on its fin.[2]
The sole Antilope is undergoing restoration in a private museum, owned by the Association Antilope, at Montpelier-Mediterranee Airport, in southern France.[3]
Specifications (S.2510)
Data from Jane's All the World's Aircraft 1966-67[1] (projected production variant S.2510, estimated at maximum takeoff weight).
General characteristics
- Crew: 1
- Capacity: 4/5
- Length: 9.015 m (29 ft 7 in)
- Wingspan: 11.11 m (36 ft 5 in)
- Height: 2.60 m (8 ft 6 in)
- Wing area: 16.21 m2 (174.5 sq ft)
- Airfoil: root: NACA 23015; tip: NACA 4411[4]
- Empty weight: 990 kg (2,183 lb)
- Max takeoff weight: 1,900 kg (4,189 lb)
- Powerplant: 1 × Turbomeca Astazou Xturboprop, 496 kW (665 shp)
- Propellers: 3-bladed Ratier-Figeac FH 76, 1.92 m (6 ft 4 in) diameter constant-speed propeller
Performance
- Maximum speed: 450 km/h (280 mph, 240 kn) at 6,100 m (20,000 ft)
- Cruise speed: 380 km/h (240 mph, 210 kn) 70% power, at 6,100 m (20,000 ft)
- Range: 2,000 km (1,200 mi, 1,100 nmi) typical max
- Service ceiling: 1,100 m (3,600 ft)
- Rate of climb: 13.5 m/s (2,660 ft/min) at sea level
References
- ^ a b c d e Taylor, John W R (1966). Jane's All the World's Aircraft 1966-67. London: Sampson Low, Marston &Co. Ltd. pp. 56–7.
- ^ "S.I.P.A. S-2510 'Antilope'". Retrieved 2010-02-27.
- ISBN 0-85130-375-7.
- ^ Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.
Further reading
- Coleman, Herbert J. (24 June 1963). "SIPA Seeks Military Orders for Antilope". Aviation Week & Space Technology. 78 (25): 96–99. Retrieved 18 April 2019AVweek
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