Engineering:Fournier RF-3
| 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 |
The Fournier RF-3 is a single-seat motor glider designed by René Fournier and first flown in 1960.
Design and development
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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
- 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.
External links
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