From Wikipedia, the free encyclopedia
B.260 Anjou
|
Role
|
Civil utility aircraft
Type of 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
American
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
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]
- 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)
[
edit
]
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 m
2
(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 Regnier 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)
- Take-off run:
160 m (520 ft)
- Landing run:
150 m (490 ft)
References
[
edit
]
- ^
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
[
edit
]
- Taylor, Michael J. H. (1989).
Jane's Encyclopedia of Aviation
. London: Studio Editions. p. 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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]