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Mathis Vega 42

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Vega 42
Type Radial engine
National origin France
Manufacturer Société Mathis Aviation
Designer Émile E. C. Mathis / Raymond Georges
First run 1938

The Mathis Vega 42 was a 42-cylinder 6-bank in-line radial piston engine, designed and built in France, by Société Mathis Aviation in the late 1930s, with development continuing during and after WWII.

Design and development

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Émile E. C. Mathis had begun designing and producing motor-cars from 1910. Société Mathis Aviation, formed in 1937, began designing aircraft engines, initially with the large and complex Vega.[1]

The Vega (and the similar Vesta) had a 2-piece Aluminium-alloy crankcase, 7 Aluminium-alloy cylinder blocks, with one-piece Aluminium-alloy heads and steel cylinder liners. A 6-throw crankshaft ran in 7 plain bearings.

Development continued after the war, culminating in the 119.4 L (7,290 cu in) 3,700 kW (5,000 hp) Vesta 42, which did not reach the hardware stage before Mathis closed its doors.[1]

Operational history

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The Vega engines were run on test-beds, and some sources indicate the engine was flown 100 hours in a test bed aircraft during 1939, but no details of flight testing survive.[1]

Variants

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Vega 42A
Initial version of the engine first run in 1938, rated 1,700 kW (2,300 hp) at 3,000 rpm. Two examples and a full-scale mock-up are reported to have been built.[1]
Vega 42B
An improved variant, under development in 1940. Completed and unfinished engines were hidden from invading German forces, in the Pyrenees.[1]
Vega 42D
An enlarged capacity version which became the Vesta 42.[1]
Vega 42E
Post WWII development rated at 2,100 kW (2,800 hp) for take-off.
Vesta 42
An enlarged Vega, developed from 1942, with similar configuration, but 158 mm (6.22 in) bore, 145 mm (5.71 in) stroke and 119.4 L (7,290 cu in) displacement, rated at 3,700 kW (5,000 hp).[1][2]


Specifications (42E-00)

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Data from Old Machine Press: Mathis Vega 42-Cylinder Aircraft Engine,[1] Aircraft engines of the World 1946[2]

General characteristics

  • Type: 42 cylinder in-line radial engine (6 7-cylinder banks)
  • Bore: 125 mm (4.92 in)
  • Stroke: 115 mm (4.53 in)
  • Displacement: 59.3 L (3,620 cu in)
  • Length: 1,520 mm (59.84 in)
  • Diameter: 1,070 mm (42.13 in)
  • Dry weight: 1,180 kg (2,600 lb)
    • Maximum Brake Mean Effective Power (b.m.e.p.) 13.4 kg/cm2 (191 psi)

Components

  • Valvetrain: 1 exhaust and 1 inlet valve per cylinder driven by 7x single overhead camshafts (SOHC)
  • Supercharger: Gear-driven single-stage driven at 5.53:1, with automatic boost control.
  • Fuel system: 1x Zenith 160 2-barrel downdraught carburetor
  • Fuel type: 100/130 Octane aviation gasolene
  • Oil system: Pressure feed at 690 kPa (100 psi), dry sump using 25.1 cs (0.00418 min) viscosity oil
  • Cooling system: liquid-cooled
  • Reduction gear: Epicyclic bevel reduction gear at 0.42:1

Performance

  • Power output: Take-off:2,100 kW (2,800 hp) at 3,200 rpm at 1.2 m (3 ft 11 in) +8.6lb boost
Normal:1,700 kW (2,300 hp) at 3,000 rpm at 2,000 m (6,600 ft)
Cruising:1,300 kW (1,700 hp) at 2,500 rpm at 2,000 m (6,600 ft)

See also

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References

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  1. ^ a b c d e f g h Pearce, William (5 December 2018). "Mathis Vega 42-Cylinder Aircraft Engine". Old Machine Press. Retrieved 5 December 2018.
  2. ^ a b Wilkinson, Paul H. (1946). Aircraft engines of the World 1946 (4th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 244–245.

Further reading

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