Stinson Voyager was a 1940s American light utility monoplane built by the Stinson Aircraft Company. [1 ]
Development [ edit ]
First developed as the
Stinson Model 105 in 1939 it was a high-wing three-seat braced monoplane powered by either a 75 hp Continental A-75 or a 80 hp Continental A-80-6. This was developed into the Model 10 powered by a Continental A-80 piston engine. [1 ] The Model 10 introduced a wider cabin as well as improved standards of interior and finish. [1 ] The Model 10 was followed by the Model 10A powered by a [1 ] Franklin 4AC-99 engine and the Model 10B with a Lycoming GO-145. [1 ]
Six Model 10As were evaluated by the United States Army as the
YO-54, the successful testing led to an order for a slightly larger and heavier O-62, later designated the L-5 Sentinel. [1 ]
A number of Model 105s and Model 10As were
impressed into Army service as the AT-19 (later L-9). [2 ]
After the Second World War the type was developed as the
Model 108, the prototypes being converted Model 10As. [2 ]
Variants [ edit ]
Production variant also known as the HW-75 with a
Continental A-75 engine), or HW-80 with a Continental A-80 engine, 277 built. [2 ] Model 10
Improved production variant with a 80 hp Continental A-80 engine, 260 built.
[2 ] Model 10A
Variant with a 90 hp
Franklin 4AC-99 engine, 515 built (10A and 10B). [2 ] Model 10B
Variant with a 75 hp
Lycoming GO-145 engine, 515 built (10A and 10B). [2 ] YO-54
United States Army designation for six Model 10s for evaluation.
[3 ] AT-19A
Original military designation for eight Model 105s impressed in 1942, later changed to L-9A.
[4 ] AT-19B
Original designation for 12 impressed Model 10A Yoyagers, later changed to L-9B.
[4 ] L-9A
Final designation for eight impressed Model 105 Voyagers, originally AT-19A.
[4 ] L-9B
Final designation for 12 impressed Model 10A Yoyagers, originally AT-19B.
Operators [ edit ]
Specifications (105) [ edit ]
Data from General Dynamics Aircraft and their Predecessors [5 ]
Capacity: 2 passengers
Length: 22 ft 2 in (6.76 m)
Wingspan: 34 ft 0 in (10.36 m)
Height: 6 ft 6 in (1.98 m)
Wing area: 155 sq ft (14.4 m 2)
NACA 4412 Airfoil:
Empty weight: 923 lb (419 kg)
Gross weight: 1,580 lb (717 kg)
Powerplant: 1 × Continental A-75-3 air-cooled flat-four, 75 hp (56 kW)
Maximum speed: 105 mph (169 km/h; 91 kn)
Cruise speed: 100 mph (87 kn; 161 km/h)
Range: 350 mi (304 nmi; 563 km)
Service ceiling: 10,500 ft (3,200 m)
Rate of climb: 430 ft/min (2.2 m/s)
See also [ edit ]
References [ edit ]
^ a b c d e f Orbis 1985, p. 2960.
^ a b c d e f Simpson 1991, pp. 317–318,
^ Andrade 1979, p. 139.
^ a b c d Andrade 1979, p. 130.
^ Wegg 1990, p. 139.
U.S.Military Aircraft Designations and Serials since 1909. Leicester, UK: Midland Counties Publications, 1979. ISBN 0-904597-22-9.
The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). London: Orbis Publishing, 1985. Simpson, R.W.
Airlife's General Aviation. Shrewsbory, Shrops, UK: Airlife Publishing, 1991. ISBN 1-85310-194-X. Wegg, John.
General Dynamic Aircraft and their Predecessors. London: Putnam, 1990. ISBN 0-85177-833-X.
External links [ edit ]