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Canadair CX-131 / CL-84 Dynavert

The Canadair CL-84 Dynavert, designated by the Canadian Forces as the CX-131, was a V/STOL turbine tilt wing monoplane designed and manufactured by Canadair between 1964 and 1972.

Only four of these experimental aircraft were built with three entering flight testing.

Two of the CL-84s crashed due to mechanical failures, with no fatalities occurring in either of the accidents.

Despite the fact that the CL-84 was successful in the experimental and operational trials carried out between 1972 and 1974 however, none of the prospective customers placed any orders for the type.

Between 1957 and 1963, Canadair carried out research in VTOL technology with the assistance of the National Research Board and the Defence Research Board of Canada.

The studies pointed the way to a unique tilt-wing design.

The wing and the power plants of the aircraft could be tilted hydro-mechanically, so that the wing incidence changed through 100 degrees from a normal flight angle to those for STOL and VTOL.

The incidence of the tail plane was automatically altered to deal with trim changes as the wing-incidence varied.

The two sets of tail rotor blades were locked in a fore and aft position in conventional flight.

The design team included Canadair’s chief designer, Frederick Phillips and Karlis Irbitis as well as many other designers.

At the time of the CL-84 project, Canadair was a subsidiary of General Dynamics and the parent company christened the new aircraft, the Dynavert.





12 passengers


47 ft 3.5 in (14.415 m)


34 ft 4 in (10.46 m)


14 ft 3 in (4.34 m)

Wing area

233.3 sq ft (21.67 m2)


NACA 633-418

Empty weight

8,417 lb (3,818 kg)

Max take-off 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)


2 × Lycoming T53 shaft-turbines, 1,500 shp (1,100 kW) each

Main rotor diameter

14 ft 0 in (4.27 m)


4-bladed, 14 ft 0 in (4.27 m) diameter


Maximum speed

321 mph (517 km/h, 279 kn)

Cruise speed

301 mph (484 km/h, 262 kn)

Never exceed speed

415 mph (668 km/h, 361 kn)


421 mi (678 km, 366 nmi) with max wing fuel, VTOL, & 10% reserves

Rate of climb

4,200 ft/min (21 m/s)

Disc loading

195 kg/m2

Power loading

1.35 kg/kW.




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