Engineering:Boisavia Anjou
| B.260 Anjou | |
|---|---|
| Role | Civil utility aircraft |
| Manufacturer | Boisavia, SIPA |
| First flight | 2 June 1956 |
| Number built | 1 |
The Boisavia B.260 Anjou (later developed by SIPA as the Sipavia Anjou) was a four-seat twin-engine light aircraft developed in France in the 1950s. It was a low-wing cantilever monoplane of conventional configuration with retractable tricycle undercarriage. Intended by Boisavia as a touring aircraft, it did not find a market and only the single prototype was constructed. At this point, the firm sold the design to SIPA, which modified the design and re-engined it with Lycoming O-360 engines, but found that they could not sell it either. At a time when the twin-engine light plane market was already dominated by all-metal United States aircraft, the Anjou's fabric-over-tube construction was something of an anachronism, and all development was soon ceased. Plans to develop a stretched version with three extra seats and Potez 4D engines were also abandoned.
Variants
- B.260 - Boisavia prototype with Regnier 4L engines (1 built)
- S.261 - SIPA conversion with Lycoming O-360 engines (1 converted)
- S.262 - Planned seven-seat version (not built)
Specifications (B.260)
Data from Jane's All the World's Aircraft 1958-59 [1]
General characteristics
- Crew: 1
- Capacity: 3 pax
- Length: 7.2 m (23 ft 7 in)
- Wingspan: 13 m (42 ft 8 in)
- Height: 3 m (9 ft 10 in)
- Wing area: 21.5 m2 (231 sq ft)
- Aspect ratio: 7.6
- Empty weight: 1,300 kg (2,866 lb)
- Gross weight: 2,000 kg (4,409 lb)
- Fuel capacity: 450 L (118.9 US gal; 99.0 imp gal) in two wing tanks + 2x 100 L (26.4 US gal; 22.0 imp gal) optional wing-tip tanks
- Powerplant: 2 × SNECMA Régnier 4L-02 4-cylinder air-cooled inverted in-line piston engines, 130 kW (170 hp) each
- (SNECMA licence-built )
- Propellers: 2-bladed fixed-pitch propellers
Performance
- Maximum speed: 300 km/h (190 mph, 160 kn)
- Cruise speed: 240 km/h (150 mph, 130 kn) (economical)
- Stall speed: 90 km/h (56 mph, 49 kn)
- Range: 1,500 km (930 mi, 810 nmi)
- Service ceiling: 6,800 m (22,300 ft)
- Rate of climb: 6 m/s (1,200 ft/min)
- 0.833 m/s (3 ft/s) on one engine at 1,500 m (4,900 ft)
- 0.833 m/s (3 ft/s) on one engine at 1,500 m (4,900 ft)
- Take-off run: 160 m (520 ft)
- Landing run: 150 m (490 ft)
References
- ↑ Bridgman, Leonard, ed (1957). Jane's All the World's Aircraft 1958-59. London: Jane's All the World's Aircraft Publishing Co. Ltd.. p. 143.
Further reading
- Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. pp. 192.
- World Aircraft Information Files. London: Bright Star Publishing. pp. File 890 Sheet 73.
- Simpson, R. W. (1995). Airlife's General Aviation. Shrewsbury: Airlife Publishing. pp. 370, 408–09.
External links
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