DINFIA IA 46

The DINFIA IA 46 Ranquel, IA 46 Super Ranquel, and IA 51 Tehuelche were Argentine utility aircraft developed in the late 1950s.

IA 46 Ranquel/Super Ranquel and IA 51 Tehuelche
I.A. 46 Super Ranquel at Buenos Aires - San Justo airfield in April 1975.
Role Utility and agricultural aircraft
Manufacturer DINFIA
First flight 23 December 1957[1]
Introduction 1958
Status examples still in service
Primary user aero clubs
Number built 132 (IA-46)
1 (IA-51)

Development and construction

The intention was to create a light aircraft suitable for aeroclub and agricultural use, and the resulting design was a conventional high-wing strut-braced monoplane with fixed tailwheel undercarriage. The aircraft were named for the Ranquel and Tehuelche peoples, different groups indigenous to Patagonia.

The state-owned Dinfia organisation commenced production of the Ranquel at Cordoba in 1958. Construction was of a fabric-covered tubular structure, although the Tehuelche featured metal-covered wings. Accommodation was provided for a single pilot and a passenger in tandem configuration. In all, some 132 aircraft were built, some of which served as glider tugs for the Fuerza Aerea Argentina.

Production ended in December 1968.[2]

Operational history

Examples of the IA.46 have served aero clubs from 1958 to date, with several remaining in operation in the late 2000s.

Variants
IA 46 Ranquel
Initial production version with Lycoming O-320-A2B engine, one prototype and 115 production aircraft built.
IA 46 Super Ranquel
Version of IA 46 with Lycoming O-360-A1A engine, 16 built.
IA 51 Tehuelche
Version with metal-covered wings, larger flaps, and fuel capacity increased to 500 L (130 US gal). One built, first flown on 16 March 1963.

Operators
 Argentina

Specifications (IA 46 Ranquel)

Data from Jane's All The World's Aircraft 1965–66[1]

General characteristics

  • Crew: 1
  • Capacity:
    • 2 passengers or
    • tank for 400 L (110 US gal; 88 imp gal) chemicals
  • Length: 7.45 m (24 ft 5 in)
  • Wingspan: 11.60 m (38 ft 1 in)
  • Height: 2.15 m (7 ft 1 in)
  • Wing area: 18.0 m2 (194 sq ft)
  • Airfoil: NACA 23012
  • Empty weight: 630 kg (1,389 lb)
  • Max takeoff weight: 1,160 kg (2,557 lb)
  • Fuel capacity: 140 L (37 US gal; 31 imp gal)
  • Powerplant: 1 × Lycoming O-320-A2B air-cooled flat-four engine, 110 kW (150 hp)
  • Propellers: 2-bladed Sensenich fixed-pitch metal propeller

Performance

  • Maximum speed: 180 km/h (110 mph, 97 kn)
  • Cruise speed: 162 km/h (101 mph, 87 kn)
  • Range: 650 km (400 mi, 350 nmi)
  • Endurance: 4 hr
  • Service ceiling: 4,000 m (13,000 ft)
  • Rate of climb: 2.40 m/s (472 ft/min)
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References
Notes
  1. Taylor 1965, p. 4.
  2. Taylor 1969, p. 3.
Bibliography
  • Taylor, John W. R. (1965). Jane's All The World's Aircraft 1965–66. London: Sampson Low, Marston & Company.
  • Taylor, John W. R. (1969). Jane's All The World's Aircraft 1969–70. London: Sampson Low, Marston & Company.
  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. p. 326.
  • Simpson, R. W. (1995). Airlife's General Aviation. Shrewsbury: Airlife Publishing. p. 413.

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