Custer CCW-5

Custer CCW-5
Країні	Сша
Роль	5-місний легкий транспорт
Перший політ	13 липня 1953
Побудований	2

У 201 Кастер CCW-5 was a twin-engined, 5-seat aircraft of pusher configuration, which used a channel wing claimed to enable low speed flight and 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.

Джерело: Custer CCW-5 у Вікіпедії

Custer Channel Wing CCW-5 STOL Walk Around
Photographer	Bill Maloney
Localisation	Unknow
Photos	19

Custer Channel Wing CCW-5 STOL 01

Custer Channel Wing CCW-5 STOL 02

Custer Channel Wing CCW-5 STOL 03

Custer Channel Wing CCW-5 STOL 04

Custer Channel Wing CCW-5 STOL 05

Custer Channel Wing CCW-5 STOL 06

Custer Channel Wing CCW-5 STOL 07

Custer Channel Wing CCW-5 STOL 08

Custer Channel Wing CCW-5 STOL 09

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General Characteristics and Role

The Custer Channel Wing CCW-5 was an experimental American short takeoff and landing (STOL) aircraft designed to demonstrate the unique Channel Wing concept developed by Willard Custer. This unique design features a pair of semi-circular or U-shaped channels mounted on the leading edge of the wing, with the engine propellers positioned at the rear of these channels. The propellers draw air over the channels, creating a massive increase in lift even at low airspeeds, allowing the aircraft to achieve exceptionally short takeoff and landing distances. The CCW-5 was the largest and final variant built, intended for potential commercial or military use as a utility transport. The design showed significant promise in achieving STOL performance but ultimately did not enter mass production due to complexity and certification challenges.

Property	Typical Value (CCW-5)
Роль	Experimental STOL Aircraft, Utility Transport Prototype
National Origin	США
Виробник	Custer Channel Wing Corporation
First Flight	1964 (CCW-5)
команда	2 (Pilot, Co-pilot)
Capacity	3 passengers (or cargo)
Довжина	8.43 m (27 ft 8 in)
Wingspan (Conventional)	12.42 m (40 ft 9 in)
зріст	2.69 m (8 ft 10 in)
Empty Weight (Approx.)	1,814 kg (4,000 lb)
Max Takeoff Weight (Approx.)	2,722 kg (6,000 lb)

Powerplant and Performance

Engine: 2 x Lycoming O-540-A series six-cylinder, air-cooled piston engines.
Power Output (Per Engine): 194 kW (260 hp).
Maximum Speed: 320 km/h (200 mph; 170 kn).
Cruise Speed: 290 km/h (180 mph; 160 kn).
Takeoff Distance (STOL Claim): Less than 60 meters (200 ft).
Channel Wing Concept: The channels essentially use propeller thrust to create a low-pressure area over the top of the wing segment, increasing the effective camber and generating lift far in excess of conventional wings at the same airspeed.

Design Origin and Legacy

Origin: The CCW-5 was a conversion of a standard Grumman Cougar twin-engine aircraft, replacing the conventional wing and engine nacelles with the Channel Wing system.
Custer’s Patent: The Channel Wing principle was patented by Willard Custer in 1951, theorizing that the forced airflow through the semi-circular channels would create “super-circulation” and exceptional lift.
Military Interest: The US military showed brief interest in the CCW design for its potential use in forward-area resupply due to the STOL capability, but no major contracts materialized.
Status: The CCW-5 and its predecessors remain significant examples of unconventional aerodynamic experiments aimed at achieving practical vertical/short takeoff and landing (V/STOL) flight.