Birdman Atlas

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Atlas
Role Ultralight aircraft
National origin Canada
Manufacturer Birdman Enterprises
Designer Bob Lovejoy
Introduction 1980[1]
Status Production completed
Number built more than 500[2]
Developed from Eipper Quicksilver

The Birdman Atlas is a single-seat, high wing, single engine in pusher configuration, ultralight aircraft that was based upon the Eipper Quicksilver design.[1][3]

Development[edit]

The Atlas was introduced to the marketplace in 1980. Production was curtailed in about 1983 as the company concentrated on producing the newer Birdman WT-11 Chinook instead.[1]

The Atlas was a development of the Quicksilver and as such incorporated many of the Quicksilver's features, such as a 6061-T6 aluminum-framed, single-surface Dacron-covered, wire-braced high wing, with the ground wires suspended from a kingpost. The fuselage structure was also built from 6061-T6 aluminum tube.[3]

The early Atlas XC variants used weight shift for control supplemented with a rudder, whereas the later 3-A versions (for 3-Axis) utilized a conventional control system with elevator and rudder, and spoilers for roll control.[3]

Variants[edit]

Atlas 215 XC
Foot-launchable single place ultralight powered by a 20 hp (15 kW) 215 cc single cylinder Cuyuna 215 engine. Control system is weight shift, plus rudder. Landing gear includes a shimmy-damped, shock-absorbing tailwheel unit. Available in kit form.[3]
Atlas 250 XC
Foot-launchable single place ultralight powered by a 25 hp (19 kW) 250 cc twin cylinder Rotax engine. Control system is weight shift, plus rudder. Landing gear includes a shimmy-damped, shock-absorbing tailwheel unit. Available in kit form.[3]
Atlas 215 3-A
Non-foot-launchable single place ultralight powered by a 20 hp (15 kW) 215 cc single cylinder Cuyuna 215 engine. Conventional three-axis control system utilizing spoilers for roll-control. Seat is adjustable fore and aft for balance. Due to company concerns about rigging requirements it was only supplied as a completed aircraft.[3]
Atlas 250 3-A
Non-foot-launchable single place ultralight powered by a 25 hp (19 kW) 250 cc twin cylinder Rotax engine. Conventional three-axis control system utilizing spoilers for roll-control. Due to company concerns about rigging requirements it was only supplied as a completed aircraft.[3]

Specifications (Atlas 215 3-A)[edit]

Data from Janes All the Worlds Aircraft 1982-83[3]

General characteristics

  • Crew: one
  • Length: 14 ft 0 in (4.27 m)
  • Wingspan: 32 ft 0 in (9.75 m)
  • Wing area: 160 sq ft (15 m2)
  • Aspect ratio: 6.4
  • Empty weight: 208 lb (94 kg)
  • Max takeoff weight: 475 lb (215 kg)
  • Fuel capacity: 2.8 US gallons (13 litres)
  • Powerplant: 1 × Cuyuna 215 two stroke snowmobile engine, 20 hp (15 kW)
  • Propellers: 2-bladed pusher propeller

Performance

  • Maximum speed: 46 mph (74 km/h; 40 kn)
  • Cruise speed: 41 mph (36 kn; 66 km/h)
  • Stall speed: 20 mph (17 kn; 32 km/h)
  • Range: 85 mi (74 nmi; 137 km)
  • Endurance: 3 hours 6 minutes
  • Rate of climb: 350 ft/min (1.8 m/s) at 2400 feet (732 m) with 150 lb (68 kg) pilot
  • Wing loading: 3.1 lb/sq ft (15 kg/m2)

See also[edit]

Aircraft of comparable role, configuration and era

References[edit]

  1. ^ a b c Jones, Terry: Birdman WT-11 Chinook - A Cabin-Class "Ultra" Lightplane. Birdman Enterprises, 1984.
  2. ^ Taylor, John WR, Jane's All The World's Aircraft 1987-88 page 544, Janes Publishing Limited.
  3. ^ a b c d e f g h Taylor, John WR: Janes All the Worlds Aircraft 1982-83 page 625-626, Janes Publishing Company, 1982. ISBN 0-7106-0748-2