A-132 Tangará
Role Primary trainer
National origin Brazil
Manufacturer Aerotec S/A Indústria Aeronáutica
First flight 26 February 1981
Primary user Bolivian Air Force
Number built 7
Developed from Aerotec A-122 Uirapuru

The Aerotec A-132 Tangará (originally the Uirapuru II) was a Brazilian military trainer aircraft developed from the A-122 Uirapuru of the 1960s.

Design and development

The A-132 Tangará was developed in response to a request from the Brazilian Air Force. Compared to its predecessor, the Uirapuru II had a longer fuselage, greater wingspan, larger fin, more powerful engine, and a redesigned, flat-sided fuselage. A similar aircraft with a less powerful engine was planned for the civil market. The prototype first flew on 26 February 1981.[1]

The Air Force originally had the intention to order 100 units but after a decision that the primary trainer should have tandem seats, the project was abandoned. The only orders came from the Bolivian Air Force, which ordered 6 units in 1986 and flew them until 1992. The prototype was given to the Air Force Technical Institute in 1990 where it was used for tests until 2004. It was then passed on to the Aeroclube de Sao Jose dos Campos, where it was flying with experimental restrictions, with a 200 hp (150 kW) engine from a Socata ST-10 Diplomate.

Variants

  • A-132A – Military trainer
  • A-132B – Civil version (planned)

Operators

 Bolivia

Specifications (prototype)

Data from Jane's All The World's Aircraft 1982–83[1]

General characteristics

  • Crew: 2
  • Length: 7.085 m (23 ft 3 in)
  • Wingspan: 9.00 m (29 ft 6 in)
  • Height: 2.70 m (8 ft 10 in)
  • Wing area: 13.77 m2 (148.2 sq ft)
  • Aspect ratio: 5.88:1
  • Airfoil: NACA 2415
  • Empty weight: 560 kg (1,235 lb)
  • Max takeoff weight: 860 kg (1,896 lb)
  • Powerplant: 1 × Lycoming O-320-B2B air-cooled flat-four, 119 kW (160 hp)
  • Propellers: single blade Sensenich M-74-DM-6-060 two-blade fixed pitch, 1.87 m (6 ft 1.5 in) diameter

Performance

  • Maximum speed: 238 km/h (148 mph, 129 kn) at sea level
  • Cruise speed: 174 km/h (108 mph, 94 kn) at 60% power
  • Stall speed: 72 km/h (45 mph, 39 kn) flaps down
  • Endurance: 4 hr 18 min
  • Service ceiling: 4,500 m (14,800 ft)
  • Rate of climb: 4.60 m/s (905 ft/min)

See also

Related development

References

  1. 1 2 Taylor 1982, p.11.
  • Tayor, John W. R., and Munson Kenneth. Jane's All The World's Aircraft 1981–1982 edition, London: Jane's Publishing Company Limited,1981 ISBN 0-86720-592-X
  • Siegrist, Martin (October 1987). "Bolivian Air Power — 70 Years On". Air International. Vol. 33, no. 4. pp. 170–176, 194. ISSN 0306-5634.
  • Taylor, John W. R. (1982). Jane's All The World's Aircraft 1982–83. London: Jane's Yearbooks. ISBN 0-7106-0748-2.
  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. p. 39.
This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.