Sıvı itici yakıtlı roket - Vikipedi

Sıvı yakıtlı roket motoru, oksitleyici ve yakıtı sıvı fazda olan bir roket motoru tipidir.

**Specifications**
	RL-10	HM7B	Vinci	KVD-1	CE-7.5	CE-20	YF-75	YF-75D	RD-0146	ES-702	ES-1001	LE-5	LE-5A	LE-5B
Country of origin	ABD	Fransa	Fransa	Sovyetler Birliği	Hindistan	Hindistan	Çin	Çin	Rusya	Japonya	Japonya	Japonya	Japonya	Japonya
Cycle	Expander	Gas-generator	Expander	Staged combustion	Staged combustion	Gas-generator	Gas-generator	Expander	Expander	Gas-generator	Gas-generator	Gas-generator	Expander bleed cycle （Nozzle Expander）	Expander bleed cycle （Chamber Expander）
Thrust (vac.)	66.7 kN (15,000 lbf)	62.7 kN	180 kN	69.6 kN	73 kN	200 kN	78.45 kN	88.26 kN	98.1 kN (22,054 lbf)	68.6 kN (7.0 tf)^[1]	98 kN (10.0 tf)^[2]	102.9 kN (10.5 tf)	r121.5 kN (12.4 tf)	137.2 kN (14 tf)
Mixture ratio							5.2	6.0		5.2	6.0	5.5	5	5
Nozzle ratio	40					100	80	80		40	40	140	130	110
I_sp (vac.)	433	444.2	465	462	454	443	438	442	463	425^[3]	425^[4]	450	452	447
Chamber pressure :MPa	2.35	3.5	6.1	5.6	5.8	6.0	3.68		7.74	2.45	3.51	3.65	3.98	3.58
LH₂ TP rpm									125,000	41,000	46,310	50,000	51,000	52,000
LOX TP rpm										16,680	21,080	16,000	17,000	18,000
Length m	1.73	1.8	2.2~4.2	2.14	2.14		2.8		2.2			2.68	2.69	2.79
Dry weight kg	135	165	280	282	435	558	550		242	255.8	259.4	255	248	285