| Wingspan | 28.0 m | 91.86 ft
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| Overall length | 28.15 m | 92.36 ft
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| Overall height | 8.78 m | 28.81 ft
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| Fuselage length | 26.77 m | 87.83 ft
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| Max TOW | 24,800 kg | 54,675 lb
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| Max landing weight | 24,600 kg | 54,234 lb
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| Max fuel weight | 4,200 kg | 9,259 lb
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| Max payload | 6,200 kg | 13,669 lb
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| Max cruise speed at 20,000 ft, ISA | 616 km/h | 330 kt
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| Takeoff field length | 1,219 m | 4,000 ft
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| Landing field length | 1,219 m | 4,000 ft
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| Max range with 64 passengers, ISA | 1,481 km | 800 nm
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| Propulsion |
N-250-100/-50 (2) Rolls-Royce AE 2100C axial-flow, free turbine turboprop engines rated 2,439 kW (3,271 shp) each. Engines turned Dowty six-blade, low-noise, high-efficiency, composite propellers.
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| Variants |
N-250-50 - Fifty-four passenger version. Based on the initial N-250 prototype.
N-250-100 - Stretched N-250 version that carried 60-68 passengers. Originally called the N-270. The -100 had a 0.5-meter fuselage plug in front of the wing and a one-meter plug aft of the wing. This version, which assumed the N-270 designation, was to have seated 70 passengers four abreast at 31-inch pitch and have a cargo area in the forward cabin. Compared to the N-250-100, the N-270 was 3.05 meters (10.0 feet) longer. Maximum take-off weight was 28,300 kilograms (62,400 lb). Maximum payload was 8,200 kilograms (18,078 lb). The N-270 was to be powered by uprated AE 2100C turboprops, rated 2,983 kW (4,000 shp) each. Range with 70 passengers was estimated at 1,481 kilometers (800 nm). IAe suspended N-270 development until certification had been received for the N-250.
N-250-200/-300 - Proposed stretched versions of the N-250. The -200 was to have been capable of carrying 76 passengers.
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