AIDC XC-2

1. 본문

The AIDC XC-2 was a prototype civil transport aircraft developed in Taiwan during the 1970s by the Aero Industry Development Corporation (AIDC).

Here are some of its key characteristics:

• Design: It was a high-wing monoplane, designed to operate from short, unprepared airstrips.
• Engines: It was powered by two turboprop engines, specifically 1400hp Lycoming T53-L-701As. Although, initial designs planned on using four engines.
• Undercarriage: The main undercarriage was housed in sponsons (external fairings) on either side of the fuselage. This design maximized the internal space.
• Fuselage: The boxy fuselage included a rear ramp for easy loading and unloading.
• Capacity:
• It was designed with a flexible internal configuration.
• Could transport up to 38 passengers.
• Could carry over 3,800 kg (8,378 lbs) of payload, or a combination of passengers and cargo.
• Performance:
• Maximum speed: 392 km/h (244 mph)
• Cruising speed: 324 km/h (201 mph)
• Range: 2,131 km (1,324 miles)
• Ceiling: 8,352 m (27,402 ft)
• Development & Production:
• AIDC started development in 1973.
• Only one prototype was built.
• It first flew on February 26, 1979.
• The aircraft was not selected for mass production.
• Context: The XC-2 project began because Taiwan's Air Force needed a medium-sized transport aircraft, and the U.S. could not export the C-130 to Taiwan.