Avro Canada CF-105 “Arrow”

The Avro Canada CF-105 Arrow was a delta-winged interceptor aircraft, designed and built by Avro Aircraft Limited (Canada) in Malton, Ontario, as the culmination of a design study that began in 1953. Considered to be both an advanced technical and aerodynamic achievement for the Canadian aviation industry, the CF-105 held the promise of Mach 2 speeds at altitudes exceeding 50,000 ft (15,000 m), and was intended to serve as the Royal Canadian Air Force’s (RCAF) primary interceptor in the 1960s and beyond.[4]

Not long after the 1958 start of its flight test program, the development of the Arrow (including its Orenda Iroquois jet engines) was abruptly and controversially halted before the project review had taken place, sparking a long and bitter political debate.[N 1][6]

The controversy engendered by the cancellation and subsequent destruction of the aircraft in production remains a topic for debate among historians, political observers and industry pundits. “This action effectively put Avro out of business and its highly skilled engineering and production personnel scattered… The incident was a traumatic one … and to this day, many mourn the loss of the Arrow

In 2010, in the context of ongoing controversy surrounding the Lockheed Martin F-35 Lightning II Canadian procurement, as an alternative to continued support of the troubled F-35, a group of individuals began lobbying Ottawa to consider domestic production of an updated version of the Avro Arrow, using modern materials and engines but keeping the Arrow’s proven “basic design”.[106] The group feels that a modernized Arrow would out-perform the F-35 in speed, range and maximum altitude, among others, while admitting that the Arrow lacks the F-35’s stealth characteristics.[107] However in 2012, the Harper government publicly rejected the bid, calling the redesigned Arrow program too risky, would take too long to develop, and be too expensive
General characteristics

Crew: 2
Length: 77 ft 9 in (23.71 m)
Wingspan: 50 ft 0 in (15.24 m)
Height: 21 ft 2 in (6.25 m)
Wing area: 1,225 ft² (113.8 m²)
Airfoil: NACA 0003.5 mod root, NACA 0003.8 tip
Empty weight: 49,040 lb (22,245 kg)
Loaded weight: 56,920 lb (25,820 kg)
Max. takeoff weight: 68,605 lb (31,120 kg)
Powerplant: 2 × Pratt & Whitney J75-P-3 turbojets
Dry thrust: 12,500 lbf (55.6 kN) each
Thrust with afterburner: 23,500 lbf (104.53 kN) each

Maximum speed: Mach 1.98 (1,307 mph, 2,104 km/h) at 50,000 ft (15,000 m) max. recorded speed; Mach 2+ potential[113]
Cruise speed: Mach 0.91 (607 mph, 977 km/h) at 36,000 ft (11,000 m)
Combat radius: 360 NM (410 mi, 660 km)
Service ceiling: 53,000 ft (16,150 m)
Wing loading: 46.5 lb/ft² (226.9 kg/m²)
Thrust/weight: 0.825 at loaded weight