Engineering:SIPA Antilope

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Antilope
SIPA Antilope F-BJSS LBG 19.06.65 edited-2.jpg
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 monoplane, seating four or five and powered by a single turboprop engine, developed in France in the early 1960s. It set a number of class records but was not put into production.

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 Fowler flaps. The fuselage was also of semi-monocoque construction. The tail unit included a variable incidence tailplane and a rudder with a trim tab.[1]

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 X turboprop, 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

  1. ↑ 1.0 1.1 1.2 1.3 1.4 Taylor, John W R (1966). Jane's All the World's Aircraft 1966-67. London: Sampson Low, Marston &Co. Ltd. pp. 56–7. 
  2. ↑ "S.I.P.A. S-2510 'Antilope'". http://www.aviafrance.com/aviafrance1.php?ID=967&ID_CONSTRUCTEUR=1140. 
  3. ↑ Ogden, Bob (2006). Aviation Museums and Collections of Mainland Europe. pp. 121–122. ISBN 0-85130-375-7. 
  4. ↑ Lednicer, David. "The Incomplete Guide to Airfoil Usage". https://m-selig.ae.illinois.edu/ads/aircraft.html. 

Further reading



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