SNECMA Atar 101

Turbojet · SNECMA
Reaction Turbines
Diameter
890 mm
Length
3680 mm
Dry Weight
940 kg
Thrust To Weight
2.98
Specific Fuel Consumption
1.05 g/(kN·s)

Architecture

Fan Fan Stages — Fan Blades — Fan Technology — Fan Pressure Ratio —
Gearbox Geared Fan No Gear — Reduction Ratio —
LP compressor Low-Pressure Compressor Stages — Low-Pressure Compressor Technology — BP Compressor Pressure Ratio —
IP compressor Intermediary-Pressure Compressor Stages — Intermediary-Pressure Compressor Technology — IP Compressor Pressure Ratio —
HP compressor High-Pressure Compressor Stages — High-Pressure Compressor Technology — HP Compressor Pressure Ratio —
Combustor Combustion Chamber Annular
HP turbine High Pressure Compressor Stages — High-Pressure Turbine Technology —
IP turbine Intermediary-Pressure Turbine Stages — Intermediary-Pressure Turbine Technology —
LP turbine Low-Pressure Turbine Stages — Low-Pressure Turbine Technology —
Whole engine Streams 1 Bypass Ratio — Overall Pressure Ratio — Afterburner No

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Airplanes

Name Aircraft Engine Number of Engines Length (m) Flat Wing Span (m)
Dassault Mystère SNECMA Atar 101 1 11.7 13.1
Dassault Super Mystère SNECMA Atar 101 1 14.13 10.51
Nord 1500 Griffon SNECMA Atar 101 1 14.54 8.1
All data (16 fields)
Name
SNECMA Atar 101
Aircraft Engine Manufacturer
SNECMA
Aircraft Engine Type
Turbojet
Dry Weight (kg)
940
Diameter (mm)
890
Length (mm)
3680
Wikipedia Article (URL)
en.wikipedia.org/wiki/SNECMA_Atar_101
Fuel
Aviation kerosene
Geared Fan
No
Combustion Chamber
Annular
Afterburner
No
Streams
1
Thrust To Weight
2.98
Specific Fuel Consumption (g/(kN·s))
1.05
Compressor Description
7-stage Axial flow
Turbine Description
Single stage Axial