SCIENTIAM QUIA OMNES

AEROSPACE ENGINEERING

ID	Country	Manufacturer	Engine	AKA	Propellant ID	Oxidiser	Fuel	Chambers	Chamber Pressure	Nozzle Diameter Initial	Nozzle Diameter Exit	Nozzle Expansion Ratio	Engine Weight	Vacuum Thrust	V Thrust Weight Ratio	Sea Level Thrust	SL Thrust Weight Ratio
1	NZL	Rocket Lab	Curie	-	HP	Mono	-	1	5,900	0.38	1.20	10 : 1	10.00	0.14	1.42	0.12	1.22
2	NZL	Rocket Lab	Rutherford	-	LOx-Kerosene	Liquid	Liquid	1	5,900	0.42	1.20	8 : 1	35.00	21.33	62.15	18.00	52.44
ID	Country	Manufacturer	Engine	AKA	Propellant ID	Oxidiser	Fuel	Chambers	Chamber Pressure	Nozzle Diameter Initial	Nozzle Diameter Exit	Nozzle Expansion Ratio	Engine Weight	Vacuum Thrust	V Thrust Weight Ratio	Sea Level Thrust	SL Thrust Weight Ratio