Fournier RF-3

The Fournier RF-3 is a single-seat motor glider designed by René Fournier and first flown in 1960.

Fournier RF-3
Belgian-registered RF-3 in 2012
Role motor glider
National origin France
Manufacturer Societé Alpavia
Designer René Fournier
First flight 1963 (RF-3)
Number built 1 (RF-1)
2 (RF-2)
89 (RF-3)
Variants Fournier RF-4

Design and development
A 1964-built RF-3 attending the 2013 LAA Rally at Sywell Aerodrome

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Fournier produced the Volkswagen-powered RF-1 single-seat motor-glider with a high-aspect ratio low-mounted wing, registered F-WJGX it first flew on 6 July 1960.[1] Fournier followed it with an improved variant, the RF-2 using a Rectimo AR.1200 engine, the first of two-built, with the help of Centre Est, first flew in June 1962.[1]

Fournier started a company Societé Alpavia to manufacture a production variant of the RF-2, named the RF-3.[1] The first RF-3 was exhibited at the June 1963 Paris Air Show. Series production commenced later that year.

An aerobatic variant with a strengthened airframe was produced as the Fournier RF-4.

Variants
RF-1
Prototype Avions Planeur first flown in 1960, one built.[1]
RF-2
Improved variant, first flown in 1962, two built.[1]
RF-3
Production variant first flown in 1963, 89 built by Alpavia at Gap-Tallard.[1]

Specifications (RF-3)

Data from Jane's All The World's Aircraft 1965–66[2]

General characteristics

  • Crew: 1
  • Length: 6.00 m (19 ft 8 in)
  • Wingspan: 11.20 m (36 ft 9 in)
  • Wing area: 11.0 m2 (118 sq ft)
  • Aspect ratio: 11.4:1
  • Airfoil: NACA 23015 at root, NACA 23012 at tip
  • Empty weight: 240 kg (529 lb)
  • Max takeoff weight: 350 kg (772 lb)
  • Fuel capacity: 30 l (6.6 imp gal; 7.9 US gal)
  • Powerplant: 1 × Rectimo air-cooled horizontally-opposed four-cylinder piston engine, 29 kW (39 hp)

Performance

  • Maximum speed: 190 km/h (120 mph, 100 kn)
  • Cruise speed: 160 km/h (99 mph, 86 kn) (econ cruise)
  • Stall speed: 70 km/h (43 mph, 38 kn)
  • Never exceed speed: 270 km/h (170 mph, 150 kn)
  • Range: 500 km (310 mi, 270 nmi)
  • Service ceiling: 5,800 m (19,000 ft)
  • Rate of climb: 4.0 m/s (790 ft/min)
  • Rate of sink: 1.20 m/s (236 ft/min) (engine off)
  • Take-off run to 15 m (50 ft): 270 m (886 ft)
  • Landing run from 15 m (50 ft): 230 m (755 ft)

References
  1. Simpson 1991, pp. 153-154
  2. Taylor 1965, p. 30.
  • Simpson, R.W. (1991). Airlife's General Aviation. Shrewsbury, England: Airlife Publishing. ISBN 1-85310-194-X.
  • Taylor, John W. R. (1965). Jane's All The World's Aircraft 1965–66. London: Sampson Low, Marston & Company, Ltd.


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