Custer CCW-5: Difference between revisions
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''American Aviation'' 17 Nov 1958 quotes similar figures: empty weight 2900 lb, normal gross 5400 lb, "maximum allowable" gross 6000 lb, 200 gallons fuel, cruise 180 mph (the two engines were 240 hp IO-470s) and range 1680 miles. Climb 3000 feet/minute, land at 15 mph, takeoff and landing distance 100 feet (weight not given). |
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Revision as of 21:30, 1 August 2013
| CCW-5 | |
|---|---|
| |
| Role | 5-seat light transport |
| National origin | USA |
| Manufacturer | Custer Channel Wing Corporation, Hagerstown, Maryland |
| First flight | 13 July 1953 |
| Number built | 2 |
The Custer CCW-5 was a twin-engined, 5-seat aircraft of pusher configuration, which used a channel wing claimed to enable low speed flight and very short take offs. Two CCW-5s flew, eleven years apart, but the type never entered production.
The aircraft was the third and last of a series of Custer Channel Wing designs.
Design and development
In most situations an aircraft's lift comes chiefly from the low pressure generated on the upper surface by the locally enhanced higher air velocity. This latter may be the result of the movement of the aircraft through the air or, when lift at low air speeds is important for short take-off performance, produced by engine power. The channel wing, the brainchild of Willard Ray Custer, increased the upper surface velocity in a U-shaped channel formed out of the wing, with a pusher propeller at the trailing edge. This near semi-circular channel laterally constrained the airflow produced by the propeller, even when the aircraft was at rest, producing higher flow velocities than over a conventional pusher wing. The need for wing mounted pusher engines made a pusher twin a natural configuration, and for his third channel wing design Custer chose to modify the existing Baumann Brigadier, a 5-seat mid wing pusher twin which itself did not reach production.[1][2]
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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.[1][2]
The first of two CCW-5s flew on 13 July 1953, piloted by Walker Davidson, at Oxnard, California[1][2] and was reported to have completed its test flying by autumn 1956, when production was scheduled to begin.[1] This did not happen, though a second aircraft flew in June 1964.[2] 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).[2] 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).[1]
The second CCW-5 airframe was finished in 1964 with 260 hp (194 kW) Continental IO-470P engines,[3] it survives and is under restoration at the Mid-Atlantic Air Museum, Reading, Pennsylvania.
Specifications
Data from [1]
General characteristics
- Crew: 1
- Capacity: 4 passengers
- Length: 28 ft 8.5 in (8.750 m)
- Wingspan: 41 ft 2 in (12.55 m)
- Height: 10 ft 10 in (3.30 m)
- Empty weight: 3,000 lb (1,361 kg) design weight
- Gross weight: 5,400 lb (2,449 kg) design weight
- Powerplant: 2 × Continental O-470-A flat 6-cylinder air-cooled, 225 hp (168 kW) each
Performance
- Maximum speed: 220 mph (350 km/h, 190 kn) [2]
- Cruise speed: 180 mph (290 km/h, 160 kn) [2]
- Range: 1,680 mi (2,700 km, 1,460 nmi) [2]
- Service ceiling: 20,000 ft (6,100 m) [2]
American Aviation 17 Nov 1958 quotes similar figures: empty weight 2900 lb, normal gross 5400 lb, "maximum allowable" gross 6000 lb, 200 gallons fuel, cruise 180 mph (the two engines were 240 hp IO-470s) and range 1680 miles. Climb 3000 feet/minute, land at 15 mph, takeoff and landing distance 100 feet (weight not given).
Notes
References
- "Aerofiles: Custer". Retrieved 2010-04-03.
- Bridgman, Leonard (1956). Jane's All the World's Aircraft 1956-57. London: Jane's All the World's Aircraft Publishing Co. Ltd.
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