The Canadair CL-84, begun in November 1963, was a quarter the size of the XC-142. It weighed 8,100 lb empty, could make a vertical take-off at 12,200 lb, or a shorttake-off at 14,700 lb. The wings were 33 ft long and housed two 1,450 shp Lycoming T53-LTC1K-4A turboprops which powered the cross-linked 14 ft four-bladed propellers. Pitch control was provided by two counter-rotating two-bladed horizontal propellers, which in horizontal flight were stopped and aligned to minimize drag. Roll control was by differential pitch, and yaw was controlled with ailerons.

It made its first vertical flight in May 1965, and first conventional flight that December. A total of four aircraft were built, including one which was not flown. US pilots evaluated it extensively, including demonstrations on amphibious ships and the Pentagon helipad. Neither government was sufficiently interested to order production aircraft. Two aircraft were destroyed in non-fatal accidents due to mechanical failures.

Source: AHS V/STOL Wheel

Overview

Data on design, manufacture and status

Design authority: Canadair Ltd

Primary manufacturer: Canadair Ltd

Parent type: Canadair CL-84

Aircraft status: No longer flying

Configuration

Primary flight and mechanical characteristics

VTOL type: Convertiplane

Compound type: N/A

Lift configuration: Tilt wing (x2)

Dedicated control device: Tail rotor

Crew required: TBA

Crew seating: Side-by-side

Landing gear: Wheels (all retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height:  
Overall Length:  
Overall Width:  
Airframe Dimensions
Airframe Length:  
Airframe Width:  
Airframe Height:  
Landing Gear Dimensions
Landing Gear Base:  
Landing Gear Track:  
Cabin Dimensions
Cabin Internal Height:  
Cabin Internal Length:  
Cabin Internal Width:  

Weights and Performance

Data on aircraft weight and flight characteristics

Weights
Max Gross Weight (ground): 5,082 kg 11,203 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 5,082 kg 11,203 lb
Empty Weight:  
Useful Load:  
Empty Weight Fraction:  
Climb Performance
Max Rate of Climb:  
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Limitations
Max Level Flight Speed:  
Never Exceed Speed:  
Service Ceiling:  
Range and Endurance
Max Range:  
Max Endurance:  

Engine Details

Aircraft powerplant (lift and/or propulsion)

Provided powerplant data is for uninstalled, sea level, static operations.

Powerplant
Number of engines: 2
Normal Ratings
Max continuous:  
Take-off / rated:  
Intermediate:  
Maximum:  
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

Main Rotor Characteristics
Diameter:  
RPM:  
Direction of Rotation: Unknown
Hub Type:
Main Rotor Blade Characteristics
Blade Construction:
Blade Chord:  
Blade Tip Geometry:
Blade Twist:  
Number of Blades: 4
Main Rotor Derived Characteristics
Disc Area:  
Disc Loading:  
Solidity:  
Main Rotor Blade Derived Characteristics
Blade area per blade:  
Tip Speed:  

Primary Control Device

Data on primary control devices such as tail rotors

The tail rotor actually comprised two contra-rotating two blade rotors that provided pitch control in low-speed flight. In forward flight these wre stopped and aligned, fore and aft along the aircraft, to minimize drag.

Tail Rotor Characteristics
Diameter:  
Configuration: Unknown
Direction of Rotation: Unknown
RPM:  
Tail Rotor Blade Characteristics
Number of Blades: 4
Blade Construction:  
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area:  
Solidity:  
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade):  

Related VFS Resources

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Related Public Resources

Resources related to the CL-84 Dynavert, provided by public sources across the internet.

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