Canadair CL-84

Canadair CL-84

was a V/STOL turbine tilt-wing monoplane designed and manufactured by Canadair. Only four of these experimental aircraft were built with three entering flight testing.

Role : experimental VSTOL
National origin : Canada
Manufacturer : Canadair
Designed by : Frederick C. Phillips
First flight : 7 May 1965
Introduced : in test evaluation
Retired : 1974
Status : retired
Primary user : Royal Canadian Air Force (intended)
Produced : 1964–1972
Number built : 4

Canadair CL-84 Specifications

General characteristics

  • Crew: 2
  • Capacity: 12 passengers
  • Length: 47 ft 3.5 in (14.415 m)
  • Wingspan: 34 ft 4 in (10.46 m)
  • Height: 14 ft 3 in (4.34 m)
  • Wing area: 233.3 sq ft (21.67 m2)
  • Airfoil: NACA 633-418
  • Empty weight: 8,417 lb (3,818 kg)
  • Max takeoff weight: 14,500 lb (6,577 kg) (STOL), 12,600 lb (5,710 kg) (VTOL)
  • Maximum width over propeller tips:34 ft 8 in (10.56 m)
  • Maximum height over propellers during wing tilt: 17 ft 1½ in (5.22 m)
  • Powerplant: 2 × Lycoming T53 shaft-turbines, 1,500 shp (1,100 kW) each
  • Main rotor diameter: 7 ft 0 in (2.13 m)
  • Propellers: 4-bladed, 14 ft 0 in (4.27 m) diameter

Performance

  • Maximum speed: 321 mph (517 km/h; 279 kn)
  • Cruise speed: 301 mph (262 kn; 484 km/h)
  • Never exceed speed: 415 mph (361 kn; 668 km/h)
  • Range: 421 mi (366 nmi; 678 km) with max wing fuel, VTOL, & 10% reserves
  • Rate of climb: 4,200 ft/min (21 m/s)
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