From Wikipedia, the free encyclopedia
Prototype transport aircraft by the Aerospace Industrial Development Corporation
The
AIDC XC-2
was a prototype civil transport aircraft designed in the 1970s in
Taiwan
. It was a high-wing
monoplane
powered by two
turboprop
engines. The main
undercarriage
was carried in
sponsons
on either side of the boxy
fuselage
, maximising internal space.
A single prototype was built and was not selected for production.
Specifications (performance estimated)
[
edit
]
Data from
Jane's All The World's Aircraft 1980-81
[2]
General characteristics
- Crew:
3 (pilot, co-pilot and flight engineer)
- Capacity:
38 passengers
or
3,855 kg (8,500 lb) cargo
- Length:
20.10 m (65 ft 11 in)
- Wingspan:
24.90 m (81 ft 8 in)
- Height:
7.72 m (25 ft 4 in)
- Wing area:
65.40 m
2
(704.0 sq ft)
- Aspect ratio
:
9.5:1
- Airfoil
:
NACA 65
3
-218
- Empty weight:
7,031 kg (15,501 lb)
- Max takeoff weight:
12,474 kg (27,500 lb)
- Fuel capacity:
3,028 L (666 imp gal; 800 US gal)
- Powerplant:
2 ×
Lycoming T53
-L-701A
turboprops
, 1,082 kW (1,451 hp) each
- Propellers:
3-bladed Hamilton Standard 53C51-17
variable-pitch propellers
, 3.05 m (10 ft 0 in) diameter
Performance
- Maximum speed:
392 km/h (244 mph, 212 kn) at sea level
- Cruise speed:
333 km/h (207 mph, 180 kn) at 3,050 m (10,000 ft) (econ. cruise)
- Stall speed:
145 km/h (90 mph, 78 kn) (flaps down)
- Never exceed speed
:
463 km/h (288 mph, 250 kn)
- Range:
1,661 km (1,032 mi, 897 nmi) with maximum fuel
- Service ceiling:
8,015 m (26,296 ft)
- Rate of climb:
7.6 m/s (1,500 ft/min)
- Takeoff run to 15 m (50 ft):
778 m (2,552 ft)
- Landing run from 15 m (50 ft):
826 m (2,710 ft)
See also
[
edit
]
Aircraft of comparable role, configuration, and era
References
[
edit
]
Further reading
[
edit
]
- Taylor, Michael J. H. (1989).
Jane's Encyclopedia of Aviation
. London: Studio Editions. p. 44.
External links
[
edit
]
Wikimedia Commons has media related to
AIDC XC-2
.