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	IRN	Iranian Space Agency	Nazeat-6H-A	-	AP-HTPB-Al	Solid	Solid	1	4,800	0.06	0.36	31 : 1	440.00	642.27	148.84	604.80	140.16
2	IRN	Iranian Space Agency	Safir-1	-	NTO-UDMH	Liquid	Liquid	1	5,900	0.24	1.35	31 : 1	1,350.00	225.00	16.99	192.61	14.55
3	IRN	Iranian Space Agency	Safir-2	-	NTO-UDMH	Liquid	Liquid	4	5,900	0.24	1.35	31 : 1	200.00	40.00	20.39	34.24	17.46
4	IRN	Iranian Space Agency	Safir-3	-	AP-HTPB-Al	Solid	Solid	1	5,900	0.24	1.35	31 : 1	50.00	8.00	16.31	6.85	13.97
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