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Northrop C-19 Alpha

From Wikipedia, the free encyclopedia

YC-19 Alpha
Northrop Alpha (Y1C-19).jpg
Northrop Y1C-19
Role Transport
Manufacturer Northrop
Designer John K. Northrop
First flight 1930 (Northrop Alpha)
Introduction 1931
Primary user US Army Air Corps
Number built 3[1]
Developed from Northrop Alpha

The Northrop C-19 Alpha was a series of three aircraft purchased from Northrop by the US Army Air Corps in 1931. They were slightly modified versions of the civil Northrop Alpha Type 2.[1]

Design and development

The YC-19 aircraft were Northrop Alpha 4s supplied for evaluation to the USAAC. No production orders were given.[1] The major difference between the C-19s and the Alphas was that the civilian version carried a pilot and six passengers while the Army version carried a pilot and four passengers.

Operational history

One aircraft, the last of the three purchased, crashed between Richmond and Petersburg, Virginia on Sunday, March 19, 1933, killing its pilot and two passengers.[citation needed] The other aircraft were used for several more years until being sent to training schools as subjects for maintenance and repair classes.

Variants

YC-19
one aircraft, previously an Alpha 4, serial number 31-516[2]
Y1C-19
two aircraft, serial numbers 31-517 to 31-518,[2] Pratt & Whitney R-1340-11 engine[3]

Operators

Specifications (Alpha landplane)

Data from Janes all the Worlds Aircraft 1931[4]

General characteristics

  • Crew: 1
  • Capacity: 6 passengers
  • Length: 28 ft 4.5 in (8.649 m)
  • Wingspan: 41 ft 10 in (12.75 m)
  • Height: 9 ft 0 in (2.74 m)
  • Wing area: 295 sq ft (27.4 m2)
  • Airfoil: Clark Y[5]
  • Empty weight: 2,660 lb (1,207 kg)
2,900 lb (1,315 kg) Seaplane
  • Gross weight: 4,500 lb (2,041 kg)
4,700 lb (2,132 kg) Seaplane

Performance

  • Maximum speed: 170 mph (270 km/h, 150 kn)
165 mph (143 kn; 266 km/h) Seaplane
  • Cruise speed: 145 mph (233 km/h, 126 kn)
140 mph (122 kn; 225 km/h) Seaplane
  • Stall speed: 60 mph (97 km/h, 52 kn)
  • Range: 650 mi (1,050 km, 560 nmi)
  • Service ceiling: 19,300 ft (5,900 m)
18,000 ft (5,486 m) Seaplane
  • Absolute ceiling: 21,100 ft (6,431 m)
20,000 ft (6,096 m) Seaplane
  • Rate of climb: 1,400 ft/min (7.1 m/s) at sea level
650 ft/min (198 m/min) at 10,000 ft (3,048 m)
1,250 mph (1,086 kn; 2,012 km/h) Seaplane at sea level
550 ft/min (168 m/min) Seaplane at 10,000 ft (3,048 m)
  • Wing loading: 15.25 lb/sq ft (74.5 kg/m2)
15.9 lb/sq ft (78 kg/m2) Seaplane
0.0893 hp/lb (0.1468 kW/kg) Seaplane

See also

Related development

Related lists

References

  1. ^ a b c "The Complete Encyclopedia of World Aircraft" Editors: Paul Eden & Soph Moeng, (Amber Books Ltd. Bradley's Close, 74-77 White Lion Street, London, NI 9PF, 2002, ISBN 0-7607-3432-1), 1152 pp.
  2. ^ a b "United States Military Aircraft Since 1909" by F. G. Swanborough & Peter M. Bowers (Putnam New York, ISBN 0-85177-816-X) 1964, 596 pp.
  3. ^ "U.S. Army Aircraft 1908-1946" by James C. Fahey, 1946, 64pp.
  4. ^ Grey, C.G., ed. (1931). Jane's All the World's Aircraft 1931. London: Sampson Low, Marston & company, ltd. p. 303c.
  5. ^ Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.
This page was last edited on 30 June 2020, at 15:23
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