KRE-075

KRE-075
Country of originSouth Korea
DesignerKorea Aerospace Research Institute
ManufacturerHanwha Aerospace
Liquid-fuel engine
PropellantLOX / Jet A-1
Mixture ratio2.45
CycleOpen-type gas generator
Configuration
Nozzle ratio94.5
Performance
Thrust, vacuum
  • 1st stage: 735.5 kN (165,300 lbf)
  • 2nd stage: 788 kN (177,000 lbf)
Chamber pressure7.0 MPa (1,020 psi)
Specific impulse, vacuum
  • 1st stage: 298.6 s (2.928 km/s)
  • 2nd stage: 315.4 s (3.093 km/s)
Specific impulse, sea-level261.7 s (2.566 km/s)
Mass flow0.822 kg/s (108.7 lb/min)
Burn time
  • 1st stage: 127 seconds
  • 2nd stage: 148 seconds
Dimensions
Length3.4 m (11 ft)
Diameter810 mm (32 in)
Used in
Nuri first and second stage

KRE-075 is a 75-ton thrust liquid rocket engine developed by Korea Aerospace Research Institute. It was used as the first stage engine of the Nuri test launch vehicle in 2018 and as the first and second stage engines of the Nuri in 2021.

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