Statements (24)
| Predicate | Object |
|---|---|
| gptkbp:instance_of |
gptkb:engine
|
| gptkbp:bfsLayer |
6
|
| gptkbp:bfsParent |
gptkb:SNECMA_Atar_9_K-50
|
| gptkbp:compression_ratio |
20:1
|
| gptkbp:diameter |
0.9 m
|
| gptkbp:engine |
gptkb:SNECMA_Atar_9_K-30
Brayton cycle twin-spool |
| gptkbp:engine_type |
axial turbine
|
| gptkbp:fan_art |
single-stage fan
|
| gptkbp:first_flight |
gptkb:1980
|
| gptkbp:fuel_capacity |
0.85 kg/k N/h
|
| gptkbp:fuel_type |
kerosene
annular combustor |
| https://www.w3.org/2000/01/rdf-schema#label |
SNECMA Atar 9 K-50 R
|
| gptkbp:length |
3.8 m
|
| gptkbp:manufacturer |
gptkb:SNECMA
|
| gptkbp:operational_area |
gptkb:aircraft
|
| gptkbp:propulsion |
50 k N
|
| gptkbp:supports |
80 kg/s
|
| gptkbp:type |
afterburning turbojet
|
| gptkbp:used_in |
gptkb:Dassault_Mirage_2000
|
| gptkbp:variant |
Atar 9 K-50
|
| gptkbp:weight |
approximately 1,200 kg
|