Custer CCW-5 Channel Wing, Twin-pusher-engine five-seat low-wing tricycle-gear STOL prototype cabin monoplane, U.S.A.

Custer CCW-5 Channel Wing
Twin-pusher-engine five-seat low-wing tricycle-gear STOL prototype cabin monoplane, U.S.A.

Archive Photos ¹

Custer CCW-5 "Channel Wing" (N5855V) at the Mid-Atlantic Air Museum, Reading, PA (John Shupek photos)

Overview ²

The CCW-5 retained the fuselage and empennage of the Brigadier, but replaced the whole centre section with a pair of channels, starting at roots in the lower part of the fuselage. Only beyond the channels did the conventional wings regain their mid-wing configuration. A 225 hp (168 kW) Continental O-470 flat six engine was mounted on slender vertical and horizontal struts at the centre of each the channels, on the mid-wing line. These drove constant speed pusher propellers. The main undercarriage was much shortened by mounting its legs on the outer part of the channel section; the Brigadier nosewheel was retained.

The first of two CCW-5s flew on 13 July 1953, piloted by Walker Davidson, at Oxnard, California and was reported to have completed its test flying by autumn 1956, when production was scheduled to begin. This did not happen, though a second aircraft flew in June 1964. The delay was partly the result of financial problems, though the CCW-5 performed well below the original estimates, with a maximum achieved speed of 220 mph (354 km/h) compared with an estimated 300 mph (480 km/h). It was claimed that the aircraft could fly under control at 11 mph (18 km/h) and that it could take off with a 1,500 lb (680 kg) load at 70% power in 90 ft (28 m).

The second CCW-5 was finished in 1964 with 260 hp (194 kW) Continental IO-470P engines; it survives and is under restoration at the Mid-Atlantic Air Museum, Reading, Pennsylvania.

Custer CCW-5 Specifications ³

Manufacturer

Custer Channel Wing Corporation

Type

Twin-engine STOL monoplane.

Wings

Cantilever mid-wing monoplane of channel-wing configuration.
NACA 4418 airfoil section in channel, which has a chord of 6 ft 0 in (1.83 m)
All-metal two-spar structure covered with metal and glass-fiber.
Compound-curved section of channel is of glass-fiber.
Large insert ailerons.
No slots or flaps.

Fuselage

Conventional light alloy semi-monocoque structure.

Tail Unit

Conventional cantilever all-metal structure.
Trim-tab in each control surface.

Landing Gear

Retractable tricycle type with single wheel on each unit.
Nose-wheel retracts forward, main wheels inward into bottom of channels.

Power Plant

Two 260 hp Continental O-470 six-cylinder horizontally-opposed air-cooled engines.
Hartzell fully-feathering metal propellers.
Propeller diameter of 7 ft 0 in (2.13 m).

Accommodation

Pilot and four passengers in enclosed cabin.

Dimensions, External

Wing span: 41 ft 2 in (12.55 m)
Length overall: 28 ft 8½ in (8.75 m)
Height overall: 10 ft 4 in (3.3 m)

Dimensions, Cabin Internal

Max height: 4 ft 5 in (1.35 m)
Max width: 4 ft 5 in (1.35 m)

Weights

Weight empty: 3,675 lbs (1,167 kg)
Max T-O weight: 5,400 lbs (2,450 kg)

Performance at Max T-O weight

Max level speed at S/L: 200 mph (322 km/hr)
Max cruising speed: 180 mph (290 km/hr)
Min sustained level flight speed: 35 mph (56 km/hr)
Service ceiling: 22,000 ft (6,700 m)
T-O run: 50-250 ft (15.76 m)
Range: 1,680 mi (1,460 nmi; 2,704 km) ²
Landing run (approx.): 300 ft (91 m)

References

Wikipedia, the free encyclopedia. Custer CCW-5
Taylor, John W. R. Jane's All the World's Aircraft 1964-65, Custer Channel Wing Corporation: Custer CCW-5, New York: The McGraw-Hill Company, 1965, pg 208