SIPA Antilope

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]

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

• Coleman, Herbert J. (24 June 1963). "SIPA Seeks Military Orders for Antilope". Aviation Week & Space Technology. 78 (25): 96–99. Retrieved 18 April 2019AVweek{{cite journal}}: CS1 maint: postscript (link)