|Martin Model 146 during competition c. 1935, USAF photo|
|Manufacturer||Glenn L. Martin Company|
|Primary user||United States Army Air Corps (intended)|
|Developed from||Martin B-10|
Design and development
Although generally satisfied with the speed and bombload of the Martin B-10, the United States Army Air Corps expressed a requirement for a bomber with long range. Two competitions were held in 1934-35: one for fast bombers capable of flying 2,200 miles (3,500 km), and a second for the experimental prototype of a 5,000-mile (8,000 km) bomber.
The Martin 146 was built for the first competition, competing with the Boeing Model 299 (later the B-17) and Douglas DB-1 (later the B-18). Two versions were submitted for the competition, the Model 146 (actual aircraft) and the Model 146A (design only). The only significance between the two was the planform, the 146 center section was rectangular with the outer wing being tapered while the 146A had a constant taper.
The Model 146 bore a striking resemblance to the earlier Martin B-10, with the same configurations of turret and cockpits and even the same two Wright Cyclone engines – "hardly positive selling points for a customer looking for the latest technology". The biggest differences between this aircraft and the Martin 139 (B-10) was that it was wider, allowing the pilot and co-pilot to sit side by side  and was equipped with Fowler flaps, the first large aircraft equipped with them.
The Model 146 was not successful but it led the Martin company to begin research into contemporary aviation technology. Some offshoots included the innovative Martin 145 proposed for the long-range bomber competition as well as the early studies that would lead to the Model 179 (later to emerge as the wartime Martin B-26). The aircraft was eventually returned to the factory and scrapped.
Specifications (Model 146)
- Crew: four
- Length: 52 ft 0 in (15.5 m)
- Wingspan: 75 ft 1 in (22.9 m)
- Height: 15 ft 5 in (4.7 m)
- Wing area: 729 ft² (67.7 m²)
- Loaded weight: 16,000 lb (7,257 kg)
- Max. takeoff weight: 17,100 lb (7,756 kg)
- Powerplant: 2 × Wright R-1820-G5 Cyclones "Cyclone" radials, 800 hp (597 kW) each
- Maximum speed: 234 mph (203 knots, 377 km/h)
- Cruise speed: 204 mph (177 knots, 328 km/h)
- Range: 1,237 mi (1,075 nmi, 1,991km)
- Service ceiling: 28,500 ft (8,687 m)
- Wing loading: 21.95 lb/ft² (107.2 kg/m²)
- Power/mass: 0.100 hp/lb (164.5 W/kg)
- Related development
- Aircraft of comparable role, configuration and era
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