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The SNECMA M45, also called the SNECMA Mars, was a turbojet engine designed and produced by SNECMA in France during the late 1950s and early 1960s. The M45 was the precursor to a family of turbojet and turbofan engines, culminating in the collaborative Rolls-Royce/SNECMA M45H, high bypass turbofan engine.

SNECMA M45
Type	Turbojet engine
National origin	France
Manufacturer	SNECMA
Variants	Rolls-Royce/SNECMA M45H

Variants

Data from: Aircraft Engines of the World 1964/65[1]

M45A

A compact moderate thrust turbojet.

M45A-3

for civil applications.[2]

M45AF

Aft-fan turbofan engine intended for civil aircraft.

M45B

Turbojet with afterburning for military aircraft.

M45B-3

With afterburner.[2]

M45F-3

Civil non-afterburning for small airliners / business jets.[2]

M45L-1

Lightweight civil version for small business jets.[2]

SNECMA/Bristol Siddeley M45G

Afterburning turbofan engine for AFVG, from the civil M45F.[3]

Specifications (M45A)

Data from Aircraft Engines of the World 1964/65[1]

General characteristics

• Type: 2-spool turbojet engine
• Length: 1,620 mm (63.8 in)
• Diameter: 550 mm (21.7 in)
• Dry weight:

Components

• Compressor:
• Combustors: annular combustion chamber

Performance

• Maximum thrust: 19.57 kN (4,400 lbf)
• Overall pressure ratio: 16:1
• Power-to-weight ratio:

See also

Related development

• Rolls-Royce/SNECMA M45H

Related lists

• List of aircraft engines

References

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