SARA II
Role Two-seat experimental autogyro
National origin South Africa
Manufacturer Council for Scientific and Industrial Research
First flight 30 November 1972
Number built 1

The CSIR SARA II (SARA - South African Research Autogyro) is a South African two-seat experimental autogyro designed and built by the Aeronautics Research Unit of the Council for Scientific and Industrial Research.[1]

Development

As part of the support to South African aircraft manufacturing industry the ARU developed a single-seat autogyro as a research vehicle.[1] Design of the autogyro was started in 1965 and construction followed in April 1967, by 1972 the autogyro, registered ZS-UGL, was ready for tethered tests mounted on a lorry-platform, it made its first free flight on 30 November 1972 at Swartkop Air Force Base.[1] Following the test flights the autogyro was modified.[1]

Design

The autogyro had a box-like fuselage structure made from light-alloy and was fitted with twin fins and rudders with a fixed incidence tail-plane mounted between them.[1] It was fitted with a two-bladed teetering rotor, the rotor could be spun up using a shaft drive through a clutch from the engine.[1] The engine located at the rear was a 180 hp (134 kW) Continental O-360-A air-cooled engine driving a two-bladed constant-speed pusher propeller.[1] The crew sat side by side in the enclosed fuselage with dual controls, entrance is through a forward-opening glazed door on each side.[1] The landing gear was a fixed tricycle type with a self-centering and steerable nosewheel.[1]

Specifications

Data from [2]

General characteristics

  • Crew: 2
  • Length: 4.65 m (15 ft 3 in) fuselage
  • Width: 1.2 m (3 ft 11 in)
  • Max takeoff weight: 840 kg (1,852 lb)
  • Fuel capacity: 136 L (36 US gal; 30 imp gal)
  • Powerplant: 1 × Lycoming O-360-A 4-cyl. air-cooled horizontally-opposed piston engine, 130 kW (180 hp)
  • Main rotor diameter: 2 × 11.13 m (36 ft 6 in)
  • Main rotor area: 97.2 m2 (1,046 sq ft) NACA 8-H-12 section teetering rotor
  • Propellers: 2-bladed Hartzell constant-speed propeller, 1.83 m (6 ft 0 in) diameter

Performance

  • Maximum speed: 154 km/h (96 mph, 83 kn)
  • Cruise speed: 122 km/h (76 mph, 66 kn) *Min flying speed: 48 km/h (30 mph)
  • Never exceed speed: 193 km/h (120 mph, 104 kn)
  • Service ceiling: 4,267 m (13,999 ft)
  • Rate of climb: 4.066 m/s (800.4 ft/min)

See also

Related lists

References

Notes

  1. 1 2 3 4 5 6 7 8 9 Taylor 1973, pp. 174-175
  2. ↑ Taylor, John W.R., ed. (1975). Jane's all the world's aircraft, 1975-76 (66th annual ed.). New York: Franklin Watts Inc. ISBN 978-0531032503.

Bibliography

  • Taylor, John W.R., ed. (1973). Jane's All the World's Aircraft 1973-74. London, United Kingdom: Jane's Yearbooks. ISBN 0-354-00117-5.
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