Category of engines.
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Associated Engines

11D121 Korolev GOX/Kerosene rocket engine. 68.650 kN. N1 stage 1 (block A) roll control engine. Developed 196974. Gimbaling +/ 45 degree. Propellants are fed from main engine (NK15, NK33) turbopumps. Isp=313s. Chamber Pressure: 71.60 bar. More...

11D51M Kuznetsov Lox/Kerosene rocket engine. 2843 kN. N1M 1965  A. Study 1965. As described in N1 improvement study, 1965. Huge modification of Block A engines  sea level thrust increased from 175 tonnes thrust to 250 tonnes. Isp=346s. More...

11D52F Kuznetsov Lox/Kerosene rocket engine. 1961 kN. N1F 1965  B. Study 1965. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t. Isp=347s. More...

11D52M Kuznetsov Lox/Kerosene rocket engine. 2745 kN. N1M 1965  B. Study 1965. As per N1 improvement study, 1965. Thrust increased to 280 tonnes per engine. Isp=330s. More...

11D53F Kuznetsov Lox/Kerosene rocket engine. 612 kN. N1F 1965  V. Study 1965. As per N1 improvement study, 1965. Engine thrust increased and stretched propellant tanks resulting in 20% longer burn time. Isp=346s. More...

11D53M Kuznetsov Lox/Kerosene rocket engine. 735 kN. N1M 1965  V. Study 1965. As per N1 improvement study, 1965. Further increase in thrust of Block V engines. Isp=347s. Used on NIM 1965 launch vehicle. More...

11D51F Kuznetsov Lox/Kerosene rocket engine. 1918 kN. N1F 1965  A. Study 1965. As described in N1 improvement study, 1965. Block A engine thrust increased. Isp=331s. More...

17D11 Korolev Lox/Kerosene rocket engine. 86.3 kN. Buran OMS and verniers. Out of Production. Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT200K Isp=362s. More...

17D12 Korolev Lox/Kerosene rocket engine. 86.3 kN. Out of Production. Isp=362s. Version of RD58 for Buran orbital propulsion system 17D11. Used synthetic kerosene ('Sintin') for higher specific impulse. More...

17D15 Korolev GOX/Sintin rocket engine. 4 kN. Buran OMS large verniers. Out of Production. Isp=295s. Large verniers for Buran orbital propulsion system 17D11. Uses synthetic kerosene ('Sintin') for high specific impulse. Oxygen is gaseous in system. More...

5 mlbf RP4 Notional Lox/Kerosene rocket engine. 24,459 kN. Study 1963. Operational date would have been July 1977. Recoverable stage. 10% plug nozzle. Isp=299s. Used on Nova1 DAC launch vehicle. More...

8D415K Kosberg Lox/Kerosene rocket engine. 1471 kN. Designed for use in N1. Development canceled in 1960 when Korolev turned to Kuznetsov for R9 and N1 engines after continuous rows with Glushko over performance and propellant types. First flight 1966. More...

8D726 Korolev Lox/Kerosene rocket engine. 66.7 kN. GR1 Stage 3, N11GR  V. Development based on S1.5400. Isp=350s. More...

A10 Thiel Lox/Alcohol rocket engine. 2306.8 kN. Study 1942. Planned for use in A10. Unique dualthrust chamber / single nozzle design, which was later shown to be not feasible technically. Isp=247s. More...

A4 Thiel Lox/Alcohol rocket engine. 311.8 kN. Isp=239s. Used on V2 missile. Work began June 1936. Interim design, but went into production. Used 18 x 1.5 tonne thrust chambers, feeding common mixing chamber. Tested from 1939, mass production 19431945. More...

A6 Rocketdyne Lox/Alcohol rocket engine. 414.3 kN. Out of production. Isp=265s. Used on Redstone launch vehicle. First flight 1953. Developed from the XLR43NA1, an American version of the V2 singlechamber engine tested in 1945. More...

A7 Rocketdyne Lox/Hydyne rocket engine. 416.2 kN. Out of Production. Version of Redstone engine for JupiterC test vehicle, with Hydyne fuel and 140 seconds burn time. Flew 19561959. Gas generator, pumpfed. Thrust 370 kN at sea level. Isp=265s. More...

A9 Thiel Lox/Alcohol rocket engine. 288.7 kN. Single chamber engine for V2 series C, A9. Tested 194245. Isp=255s. Never went into production in Germany, but formed the basis for successful postwar American and French rocket engines. More...

AABS Rocketdyne Lox/Kerosene rocket engine. 17.779 kN. Aerospike Annular Booster and Sustainer. Pressurefed. Booster thrust 3000 to 4000 lb vac; sustainer 15002000 lb vac, 257 sec specific impulse. Isp=285s. More...

Aestus DASA/Rocketdyne Rocketdyne rocket engine. Dasa (Germany)/Rocketdyne NonToxic Shuttle OMS. Gas generator, pumpfed. Name later reapplied to storable propellant engine for Ariane 5. More...

AirLaunch Propane Engine Air Launch Lox/Propane rocket engine. 106.8 kN. Flow calibration, ignition and initial short duration tests completed in 2005 of this upper stage rocket engine with application to future small spacecraft launchers. More...

B2C Rocketdyne Lox/Kerosene rocket engine. Atlas A. Launch thrust 1374 kN. Atlas Booster. Gas generator, pumpfed. Thrust and specific impulse values are at sea level. First flight 1958. More...

D2 Polyarniy Lox/Kerosene rocket engine. 1373 kN. R3. Out of Production. Competing engine for 3000 km range IRBM design to study problems of longrange rockets. Developed from April 1947 until cancellation. Isp=288s. More...

DF1 CALT Liquid oxygen/Alcohol rocket engine. 270 kN. More...

E1 Rocketdyne Lox/Kerosene rocket engine. 1885 kN. Study 1957. Developed by USAF in late 1950's. Cancelled and decision to go direct to 1,500,000 lbf F1 as next step. Booster applications. Gas generator, pumpfed. Isp=290s. More...

ED140 Glushko rocket engine. 68 kN. Glushko built this experimental engine, the next phase of the German Lilliput concept, in 1951. Configuration led to the successful RD107 engines of the R7. More...

F1 Rocketdyne Lox/Kerosene rocket engine. 7740.5 kN. Isp=304s. Largest liquid rocket engine ever developed and flown. Severe combustion stability problems were solved during development and it never failed in flight. First flight 1967. More...

F1A Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pumpfed. Isp=310s. More...

Fastrac Huntsville Lox/Kerosene rocket engine. 269 kN. Development ended 1996. Isp=310s. Used on X34A launch vehicle. Intended to demonstrate lower cost in a reusable simple turbopump rocket engine. More...

FastTrack Notional Lox/Kerosene rocket engine. 44.1 kN. Design concept. NASA Marshall Space Flight Center prototype experimental engine that led to Fastrac lowcost engine for X34. Isp=348s. More...

Garvey Aerospike Garvey Lox/Alcohol rocket engine. Development ended 2005. Launch thrust .044 kN. Singlechamber, liquidpropellant, annular aerospike engine. More...

H1 Rocketdyne Lox/Kerosene rocket engine. 947.7 kN. Saturn l/lB. Designed for booster applications. Gas generator, pumpfed. Isp=289s. First flight 1961. More...

H1b Rocketdyne Lox/Kerosene rocket engine. 1030.2 kN. Isp=296s. First flight 1966. More...

H1c Rocketdyne Lox/Kerosene rocket engine. 1130 kN. Study Saturn IBA, Saturn IBB, 1965. Isp=296s. More...

Kestrel SpaceX Lox/Kerosene rocket engine. 30.7 kN. Upper stages. Hardware. Isp=320s. Pintle architecture, designed to be a high efficiency, low pressure vacuum engine. Fed only by tank pressure, ablatively cooled First flight 2006. More...

KS50 Glushko Lox/Kerosene rocket engine. Experimental. Development 1948. Subscale versions of a radical new engine design. This featured a flatplate injector, cylindrical combustion chamber, and a 60 atmosphere chamber pressure. More...

KSR3 Korean Lox/Kerosene rocket engine. In development. Launch thrust 122.5 kN. Pressurefed indigenous design. First flight 2002. More...

L1 Linear Aerospike Booster Rocketdyne Lox/Kerosene rocket engine. Launch thrust 889.36 kN. Gas generator, pumpfed. Thrust and specific impulse values are at sea level. More...

L2 Linear Aerospike Booster Rocketdyne Lox/Kerosene rocket engine. Launch thrust 444.63 kN. Gas generator, pumpfed. Thrust and specific impulse values are at sea level. More...

L6.55 Notional Lox/Kerosene rocket engine. 31,010 kN. Study 1963. Engines used in recoverable stage of ballistic shape; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange. Isp=330s. More...

L7.70 Notional Lox/Kerosene rocket engine. 37,007 kN. Study 1963. Engines used in recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange. Isp=335s. More...

Liberty Liberty Lox/Kerosene rocket engine. Development 19942006. Pressurefed engine. Price $ 12,000 in 1995. Used on Scorpius launch vehicle. More...

Liberty1 Notional Lox/Kerosene rocket engine. 245.2 kN. Development ended 1988. Pressurefed engine. Isp=270s. Used on Liberty launch vehicle. More...

LR10 Reaction Motors rocket engine. Viking RTVN12. More...

LR1057 Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Atlas space launchers. Out of production. Atlas Sustainer. Gas generator, pumpfed. Evolved from MA2 ICBM system. Isp=316s. First flight 1963. More...

LR1055 Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Atlas E, F. Atlas Sustainer. Gas generator, pumpfed. Separate turbopumps for each booster engine. Isp=316s. First flight 1960. More...

LR10111 Rocketdyne Lox/Kerosene rocket engine. 5.3 kN. In Production. Isp=246s. Verniers for RS27 powerplant, used on Delta boosters 19741992. More...

LR1053 Rocketdyne Lox/Kerosene rocket engine. 375 kN. Out of Production. Early version of Atlas Sustainer. Gas generator, pumpfed. Isp=308s. More...

LR17 CurtissWright Lox/Gasoline rocket engine. RATO rocket for XB45. Launch thrust 17.6 kN. Assisted takeoff power. Single thrust chamber, both regeneratively cooled and filmcooled with water, spark plug ignition, turbinepump fed. More...

LR19 CurtissWright Lox/Gasoline rocket engine. Launch thrust 44.1 kN. Experimental unit for either missiles or piloted aircraft. Single thrust chamber, regnenerativey cooled and film cooled with wateralcohol mixture. More...

LR21 CurtissWright Lox/Gasoline rocket engine. Launch thrust 266.83 kN. Turbine pumpfed, single thrust chamber unit intended for cancelled missile application. Engine designed to fit into the envelope dimensions of the German V2! More...

LR30 Reaction Motors Lox/Ammonia rocket engine. 222.6 kN. D5583. Capable rocket engine planned for use in D5583 and X15. Cancelled in favour of XLR99. More...

LR37 CurtissWright Lox/Gasoline rocket engine. 0.225 kN. Small experimental engine for ramrocket tests. Single thrust chamber, regneratively cooled with gasoline, film cooling also used, spark plug ignition. Test article only built. More...

LR39 Reaction Motors Lox/Alcohol rocket engine. 0.225 kN. Small experimental engine. Single thrust chamber, water cooled, equipped only with spark plug igntion system and propellant flow valves. Test article only built. More...

LR797 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Out of production. Designed for booster applications. Gas generator, pumpfed. Isp=282s. First flight 1957. More...

LR8RM5 Reaction Motors Lox/Alcohol rocket engine for rocketplanes. Out of Production. Launch thrust 26.67 kN. Advanced version of the LR11, 4 chambers. Engine in the X1E was modified in 1958 to increase chamber pressure to 20 atm and burn Hydyne fuel. More...

LR83NA1 Rocketdyne Lox/Kerosene rocket engine. 683 kN. Development ended 1958. Isp=282s. Planned production version of the engine for the booster of the Navaho G38 intercontinental cruise missile. More...

LR873 Aerojet Lox/Kerosene rocket engine. 733.9 kN. Study 1957. Titan 1 booster engine. Surplus Flight Engines were available for various uses in the 1960's. Isp=290s. First flight 1959. More...

LR895 Rocketdyne Lox/Kerosene rocket engine. 822.5 kN. Atlas E, F. Designed for booster applications. Gas generator, pumpfed. Separate turbopumps for each booster engine. Isp=290s. First flight 1960. More...

LR897 Rocketdyne Lox/Kerosene rocket engine. 948 kN. Atlas space launchers. Out of production. Designed for booster applications. Gas generator, pumpfed. Shared turbopumps for booster engines. Evolved from MA2 ICBM system. Isp=294s. First flight 1963. More...

LR913 Aerojet Lox/Kerosene rocket engine. 355.9 kN. Development begun 1957. Titan 1 Stage 2 major production version. Isp=308s. Proposed for second stage of Juno VA, SuperJupiter in 1959. Flown 19591965. More...

MA5A Rocketdyne Lox/Kerosene rocket engine. 2100 kN. Out of Production. Isp=296s. Atlas Engine System, an updated version of the MA5, included replacments with selected RS27 components for sealevel Isp increase of 4 secs. First flight 1991. More...

MB3J Rocketdyne Lox/Kerosene rocket engine. Out of production. Launch thrust 755.89 kN. N Booster . Gas generator, pumpfed. Joint MHI (Japan) / Rocketdyne project, evolved from MB3. Thrust and specific impulse values are at sea level. First flight 1975. More...

MB3 Press Mod Rocketdyne Lox/Kerosene rocket engine. 755.1 kN. Test 1962. Isp=285s. Used on Sea Horse launch vehicle. More...

MB31 Rocketdyne Lox/Kerosene rocket engine. 760.6 kN. Out of production. Designed for booster applications. Gas generator, pumpfed. Isp=285s. Boosted Delta A, B, C, Thor AbleStar. First flight 1960. More...

MB33 Rocketdyne Lox/Kerosene rocket engine. 866.7 kN. Out of Production. License built in Japan for H1. Isp=290s. First flight 1964. More...

Merlin 1V SpaceX Lox/Kerosene rocket engine. 411.4 kN. Hardware. Isp=342s. Upper stage version of the Merlin developed for the Falcon 9 second stage. Based on the Merlin 1C and using a regeneratively cooled combustion chamber. First flight 2009. More...

Merlin 1A SpaceX Lox/Kerosene rocket engine. 378.040 kN. First stages. Hardware. Isp=300s. Completed development in early 2005. Pintle injector concept. Replaced by Merlin 1C. First flight 2006. More...

Merlin 1C SpaceX Lox/Kerosene rocket engine. 614.7 kN. First stages. Hardware. Isp=304s. Regeneratively cooled; turbopump also provided high pressure kerosene for the hydraulic actuators. Actuated turbine exhaust nozzle provided roll control. First flight 2008. More...

Microcosm 22N Microcosm Lox/Kerosene rocket engine. 22.250 kN. First stages. Hardware. Pressurefed, ablatively cooled engine using liquid oxygen and jet fuel as propellants. Flown 1999/2001. More...

Microcosm 356N Microcosm Lox/Kerosene rocket engine. 356 kN. First stages. Hardware. Funded under AFRL SBIR Phase 1 contract of 2006. Ablative chamber, LOX/Jet A propellant engines designed for very lowcost, robust design margins. More...

Microcosm 89N Microcosm Lox/Kerosene rocket engine. 89 kN. First stages. Hardware. In 2005 tests were conducted of this lowcost ablative composite rocket engine for responsive launch vehicle applications. More...

NK19 Kuznetsov Lox/Kerosene rocket engine. N1 stage 4. Development ended 1964. Based on NK9 engine. Originally developed for the modernized second stage of the R9 (abandoned). Also to have been used on GR1 / 8K713 Stage 2. First flight 1969. More...

NK15 Kuznetsov Lox/Kerosene rocket engine. 1544 kN. N1 stage 1 (block A). Development ended 1964. On the basis of NK9 the NK15 was developed for the N1 launcher. 30 were used on the Block A (Stage 1) of the N1. Isp=318s. First flight 1969. More...

NK15F Kuznetsov Lox/Kerosene rocket engine. 2180 kN. Development 19661972. Isp=350s. Engine had only a very short nozzle, the 24 engines around the periphery were to expand along a common central plug on the first stage of a studied N1 variant. More...

NK15V Kuznetsov Lox/Kerosene rocket engine. 1648 kN. Development ended 1964. Isp=325s. Developed from the NK9. 8 engines, featuring highexpansion nozzles, used on N1 Stage 2. First flight 1969. More...

NK21 Kuznetsov Lox/Kerosene rocket engine. N1 stage 3 (block V). Out of production. Based on NK9 engine. Propellants kerosene T1 / LOX. 4 engines used in N1 stage 3 (block V). Isp=318s. Used on N1 launch vehicle. First flight 1969. More...

NK31 Kuznetsov Lox/Kerosene rocket engine. 402 kN. Isp=353s. Upgraded version of engines for N1 stage 4, with multiple ignition capability and increased operational lifetime. Mothballed in 1974. Proposed for Black Colt launch vehicle in 1993. More...

NK33 Kuznetsov Lox/Kerosene rocket engine. 1638 kN. N1F, Kistler stage 1, Taurus II stage 1. Isp=331s. Modified version of original engine with multiple ignition capability. Never flown and mothballed in 1975 after the cancellation of the N1. Resurrected for Kistler, then for Taurus. More...

NK39 Kuznetsov Lox/Kerosene rocket engine. 402 kN. N1F stage 3. Development ended 1971. Isp=352s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. More...

NK43 Kuznetsov Lox/Kerosene rocket engine. 1755 kN. N1F, Kistler stage 2. Design 1975. Isp=346s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. Resurrected for Kistler. More...

NK9 Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. R9, GR1 stage 1. Isp=327s. Reached phase of stand testing in 1965, but then RD111 selected. Later planned for 1st Stage of GR1, but that rocket also cancelled. More...

NK9V Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. N1 stage 2 / N1 stage 3 / R9 Stage 2. Developed for 2nd stage of the R9 ICBM (alternative to RD111 engine by OKB456). NK9 with increased expansion ratio. Isp=340s. First flight 1965. More...

NK9V11D53 Kuznetsov Lox/Kerosene rocket engine. 449 kN. N1 stage 3 (block V). Out of Production. Modification of NK9 engine for the N1 lunar rocket. May be identical to NK21 (stage 3). Isp=340s. More...

NK9V11D54 Kuznetsov Lox/Kerosene rocket engine. 392 kN. N1 stage 4 (block G). Out of Production. Modification of NK9 engine for the N1 lunar rocket. May be identical to NK19 (stage 4). Isp=340s. More...

OPI Methane Engine Orion Propulsion Lox/LCH4 rocket engine. 0.445 kN. Reaction control thruster for future manned spacecraft. Developed from 2001; tested 2005. More...

Orbitec Methane Engine Orbital Technologies Corporation Lox/LCH4 rocket engine. 0.133 kN. Reaction control thruster. Tested 2005. Used vortexcooled combustion process to eliminate combustion chamber heating. More...

P41 Booster Rocketdyne Lox/Kerosene rocket engine. 2.441 kN. AQM37. Target System Booster. Pressurefed. Isp=232s. First flight 1963. More...

P41 Sustainer Rocketdyne Lox/Kerosene rocket engine. 0.470 kN. AQM37. Target System Sustainer. Pressurefed. Isp=262s. First flight 1963. More...

PF RP1 Notional Lox/Kerosene rocket engine. 20,306 kN. Study 1967. Isp=275s. Used on Saturn LCBLox/RP1 launch vehicle. More...

Press Fed 25k TRW Lox/Kerosene rocket engine. 245.2 kN. Design concept 1960's. 1960's designs for 'big dumb booster'. Isp=270s. More...

RD0256HC Kosberg Lox/Kerosene rocket engine. 820 kN. Design concept 1996. Proposed variant of RD0256 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=344s. More...

RD0155 Kosberg Lox/Kerosene rocket engine. Design concept 2007. Launch thrust 902.5 kN. Engine proposed to replace RD107 in Onega and Avrora versions of the Soyuz launch vehicle. More...

RD0141 Kosberg Lox/LNG rocket engine. 2251 kN. stage 1. Developed 1998on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD0141 with larger nozzle. Isp=353s. More...

RD0142 Kosberg Lox/LNG rocket engine. 2353 kN. stage 2. Developed 1998on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD0141 with larger nozzle. Isp=369s. More...

RD0143 Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 2. Design concept 1998. Proposed variant of RD0124, replacing kerosene by liquid natural gas. Selected for stage 2 of Vozdushnyy Start project by Kompomash. Isp=372s. More...

RD0143A Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 1. Design concept 1998. Proposed single chamber variant of RD0143. Selected for stage 1 of Vozdushnyy Start project by Kompomash. Isp=370s. More...

RD0144 Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Radiation cooled nozzle extension. Isp=374s. More...

RD0149 Kosberg Lox/LNG rocket engine. 49 kN. upper stage. Developed 1998on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Variant of RD0141 with larger nozzle. Isp=370s. More...

RD0140 Kosberg Lox/LNG rocket engine. 2086 kN. stage 2. Developed 1998on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=349s. More...

RD0210HC Kosberg Lox/Kerosene rocket engine. 592 kN. Design concept 1990's. Proposed variant of RD0210 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=342s. More...

RD0229M Kosberg Lox/LNG rocket engine. 883 kN. Vozdushnyy Start stage 1. Developed 1997. Derivative of RD0229 for the propellants LOX and liquid natural gas (methane). Initial candidate for stage 1 propulsion of Vozdushnyy Start project by Kompomash. More...

RD0234CH Kosberg Lox/LCH4 rocket engine. 442 kN. Developed 1996. Proposed variant of RD0234 engine using LOXliquid methane instead of N2O4/UDMH as propellants. Isp=343s. More...

RD0234HC Kosberg Lox/Kerosene rocket engine. 516 kN. Developed 1996. Proposed variant of RD0234 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=331s. More...

RD0242HC Kosberg Lox/Kerosene rocket engine. 125 kN. Developed 1998. Proposed variant of RD0242 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=312s. More...

RD0139 Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=341s. More...

RD0245HC Kosberg Lox/Kerosene rocket engine. 214 kN. Design concept 1990's. Proposed variant of RD0245 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=320s. More...

RD0145 Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Fourchamber variant of RD0144. Isp=374s. More...

RD0256Methane Kosberg Lox/LCH4 rocket engine. 836 kN. Design concept 1996. Proposed variant of RD0256 engine using LOXliquid methane instead of N2O4/UDMH as propellants. Isp=353s. More...

RD0244HC Kosberg Lox/Kerosene rocket engine. 690 kN. Design concept 1990's. Proposed variant of RD0244 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=332s. More...

RD0103 Kosberg Lox/Kerosene rocket engine. 34.6 kN. T3, P1 aircraft by Sukhoy. Out of Production. Based on RD0102. Chamber pressure 37.3  15.7 bar. Isp=277s. More...

RD0154 Kosberg Lox/Kerosene rocket engine. 294.3 kN. Design concept 2007. Engine proposed to replace RD110 in Avrora improved version of Soyuz launch vehicle. The single chamber engine had a deployable nozzle extension for improved vacuum specific impulse. More...

RD0134 Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle variant of RD0139. Isp=358s. More...

RD0102 Kosberg Lox/Kerosene rocket engine. 39.2 kN. Yak27V aircraft by Yakovlev. Out of Production. Based on RD0101. Two ignitions possible. Chamber pressure 41,2  16,4 bar. Isp=260s. More...

RD0105 Kosberg Lox/Kerosene rocket engine. 49.4 kN. Luna 8K72, Vostok 8K72 upper stage. Out of production. Isp=316s. Developed jointly with OKB1 in nine months on the basis of OKB1'ssteering chamber from the RD107 engine. First flight 1958. More...

RD0106 Kosberg Lox/Kerosene rocket engine. 304 kN. R9 stage 2. Gas generator cycle. Isp=330s. First flight 1961. More...

RD0107 Kosberg Lox/Kerosene rocket engine. 297.9 kN. R9, Molniya 8K78, Voskhod 11A57 stage 3. Out of Production. Gas generator cycle. Isp=326s. More...

RD0108 Kosberg Lox/Kerosene rocket engine. 297.9 kN. Voskhod 11A57, Molniya 8K78 stage 3. Isp=326s. First flight 1960. More...

RD0109 Kosberg Lox/Kerosene rocket engine. 54.520 kN. 8A92 Vostok stage 3, 8K72K stage 3 (block EVostok). Out of production. Developed in 15 months. Isp=323s. First flight 1960. More...

RD0110 Kosberg Lox/Kerosene rocket engine. 297.9 kN. Soyuz 11A511, MolniyaM 8K78M. Precursor RD0107 used in 11A57 Voskhod stage 2. Modified to increase reliability. Isp=326s. First flight 1964. More...

RD0124M1 Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998. Proposed single chamber variant of RD0124. Obviously same turbopumps, but one single chamber with larger nozzle extension compared to RD0124M. Isp=359s. More...

RD0120CH Kosberg Lox/LCH4 rocket engine. 1576 kN. Design concept 1990's. Proposed variant of the RD0120 engine using liquid methane instead of hydrogen as propellant. Isp=363s. More...

RD0120MCH Kosberg Lox/LCH4 rocket engine. 1720 kN. Design concept 1990's. Proposed variant of the RD0120M engine using liquid methane instead of hydrogen as propellant. Isp=372s. More...

RD0124 Kosberg Lox/Kerosene rocket engine. 294.3 kN. In development. Isp=359s. Engine to succeed RD0110 in second stage of Soyuz. Used staged combustion; chamber pressure increased from 70 to 160 bar, specific impulse from 326 to 359 seconds First flight 2001. More...

RD012414D23 Kosberg Lox/Kerosene rocket engine. 298.640 kN. Propoed in 1993 for Angara stage 2 verniers, Kvant1 stage 1 vernier. Designed 19861990. Isp=331s. Variant of RD0124 with shortened nozzle for sealevel operation. More...

RD0124M Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998. Proposed single chamber variant of RD0124. Obviously same turbopumps, but one single chamber. Isp=348s. More...

RD0101 Kosberg Lox/Alcohol rocket engine. 39.2 kN. E50A aircraft by Mikoyan. Out of Production. Chamber pressure 42,7  22,1 bar. Specific impulse 255  248,5 sec. Isp=255s. More...

RD0132M Kosberg Lox/LNG rocket engine. 98 kN. Vozdushnyy Start stage 2. Design concept 1998. Proposed variant of RD0132, replacing hydrogen by liquid natural gas. Initially selected for stage 2 of Vozdushnyy Start project by Kompomash. More...

RD0110MD Kosberg Lox/LNG rocket engine. 245 kN. Developed 1994on. Prototype engine for tests with propellants LOX/liquified natural gas. Tests performed from 30 April 1998 on, test duration 20s. More...

RD160 Glushko Lox/LCH4 rocket engine. 19.6 kN. Upper stage. Developed 19931996. Isp=380s. Methane version of lox / kerosene upper stage engine RD161. Gimbaling +/ 6 degree in two planes. More...

RD1611 Glushko Lox/Kerosene rocket engine. 19.6 kN. Development ended 2000. Proposed for use on Soyuz M3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=360s. More...

RD1612 Glushko Lox/Kerosene rocket engine. 19.9 kN. Design concept 1990's. Proposed for use on Soyuz M3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=365s. More...

RD167 Glushko Lox/LCH4 rocket engine. 353 kN. Upper stage. Design concept 1990's. Isp=379s. Proposed upper stage engine, a methane variant of RD134. Gimbaling +/ 3 degree in two planes. Four chambers with one common turbopump. More...

RD120M Glushko Lox/Kerosene rocket engine. 850.4 kN. PacAstro2 stage 1. Out of Production. Sealevel variant of RD120 engine, similar to RD120K. Gimbaling +/ 6 degree in two planes. Isp=330s. More...

RD169 Glushko Lox/LCH4 rocket engine. 167 kN. Riksha0 stage 1. Design concept 1990's. Isp=351s. LOX/Methane engine derived from RD120. Gimbaling +/ 8 degree in two planes. In 1996 prototype development was estimated to take four years from goahead. More...

RD170 Glushko Lox/Kerosene rocket engine. 7903 kN. Energia strapon. Developed 19731985. Isp=337s. First flight 1987. Used oneplane gimablling versus the twoplane gimablling required on the RD171 of the Zenit launch vehicle. Designed for 10 reuses. More...

RD161P Glushko H2O2/Kerosene rocket engine. 24.5 kN. Soyuz M stage 3 (block LM). Developed 1993. Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M3. Version for H2O2 fuel, concentration 9698%. Isp=319s. More...

RD146 Glushko Lox/Kerosene rocket engine. 883 kN. Angara stage 2. Design concept 1993on. Sealevel variant of RD120 engine. Proposed in initial study for Angara by RKK Energia in1993. Kerosene RG1. More...

RD134 Glushko Lox/Kerosene rocket engine. 343 kN. upper stage. Design concept. Isp=357s. Proposed upper stage kerosene engine. Gimbaling +/ 3 degree in two planes. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400. More...

RD120K Glushko Lox/Kerosene rocket engine. 873 kN. Soyuz M stage 1, 2. Proposed for X34. Isp=336s. Sealevel variant of RD120. As of 1996 RD120 prototype with 1.8 m diameter had been built, development time estimated for three years. More...

RD120.03 Glushko Lox/Kerosene rocket engine. 882 kN. Design concept. Isp=353s. More...

RD171 Glushko Lox/Kerosene rocket engine. 7903 kN. Zenit stage 1. In production. Isp=337s. RD171 used twoplane gimablling versus oneplane gimablling on RD170 developed in parallel for Energia. First flight 1985. More...

RD191M Glushko Lox/Kerosene rocket engine. 1976 kN. Angara stage I. Developed 1996. Single chamber version of the RD170 / RD171. Isp=337s. More...

RD120.01 Glushko Lox/Kerosene rocket engine. 784 kN. Design concept. Isp=329s. More...

RD134R Glushko Lox/Kerosene rocket engine. 343 kN. Angara stage 2 vernier. Design concept 1993on. Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG1. More...

RD184 Glushko Lox/LCH4 rocket engine. Developed 1996on. Isp=322s. Attitude correction engine for apogee stage of Riksha1 launcher project (together with RD183). Gimbaling +/ 20 degree in two planes. More...

RD10711D511 Glushko Lox/Kerosene rocket engine. 992 kN. Soyuz 11A5110, Soyuz 11A511U0. Design 2000. Diameter is per chamber. Isp=314s. First flight 1965. More...

RD120 Glushko Lox/Kerosene rocket engine. 833 kN. Zenit stage 2. In production. Isp=350s. High altitude engine used in the Zenit second stage. First production Russian engine to be test fired in the United States (3 test burns were made). First flight 1985. More...

RD192S Glushko Lox/LCH4 rocket engine. 2128 kN. Developed 1996on. Isp=371s. Proposed variant of RD192. Staged combustion cycle with oxidizerrich gas generator. Gimbaling +/ 8 degree in two planes. More...

RD192.3 Glushko Lox/LCH4 rocket engine. 2089 kN. Developed 1996on. Proposed variant of RD192. Gas generator cycle. Gimbaling +/ 8 degree in two planes. Status 1998 was project based on RD191 protoype, development estimated for four years. Isp=341s. More...

RD192.2 Glushko Lox/LCH4 rocket engine. 1942 kN. Developed 1996on. Isp=354s. Proposed variant of RD192. Staged combustion cycle with fuelrich gas generator. Gimbaling +/ 8 degree in two planes. More...

RD192 Glushko Lox/LCH4 rocket engine. 2138 kN. Isp=356s. Proposed methanevariant of RD191. Gimbaling +/ 8 degree in two planes. In 1996 prototype development was estimated to take four years from goahead. Nozzle expansion ratio is 262/0.75=349. More...

RD190 Glushko Lox/LCH4 rocket engine. 1000 kN. Riksha0 stage 1. Developed 1996. The RD190 consists of 6 RD169 engines. Each chamber can be gimbaled individually in two planes by +/ 8 degree. Isp=351s. More...

RD185 Glushko Lox/LCH4 rocket engine. 179 kN. Riksha0 stage 2. Developed 1996. Isp=378s. Upper stage version of RD169 with larger nozzle. Gimbaling +/ 4 degree in two planes. More...

RD172 Glushko Lox/Kerosene rocket engine. 8354 kN. Zenit3 stage 1 (?). Developed 1994. Uprated version of RD171. To have been qualified for flight 1994. Isp=337s. More...

RD183 Glushko Lox/LCH4 rocket engine. 9.8 kN. Developed 1996. Isp=360s. Main engine for apogee stage of Riksha1 launcher project. Gimbaling +/ 10 degree in two planes. Nozzle expansion ratio is 75/0.055=1364. More...

RD182M Glushko Lox/LNG rocket engine. 882 kN. Vozdushnyy Start stage 1. Developed 1998. Variant of RD182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash. More...

RD182 Glushko Lox/LCH4 rocket engine. 902 kN. Riksha (1, 2) stage 1. Developed 1994. Isp=353s. Methane variant of RD120K engine. Thrust range and Isp range due to throat diameter and chamber pressure. Gimbaling +/ 6 degree in two planes. More...

RD180 Glushko Lox/Kerosene rocket engine. 4152 kN. Atlas III, Atlas V stage 1. In production. Isp=337s. First flight 2000. Twothrustchamber derivative of the fourchamber RD170 used on Zenit. More...

RD174 Glushko Lox/Kerosene rocket engine. 7905 kN. Angara stage I. Developed 1995. More...

RD173 Glushko Lox/Kerosene rocket engine. 8181 kN. Zenit3 stage 1 (?). Design concept 1990's. Uprated version of RD171 with 4 chambers, 1 turbopump and 2 gas generators. Intended for uprated Zenit named Zenit 3 Isp=337s. More...

RD191 Glushko Lox/Kerosene rocket engine. 2079 kN. Isp=337s. Proposed for stage 1 of Angara. Single chamber from 4chamber RD170 would have been cheap and fast to develop. Only reached the draft project stage by 2003. Gimbaling +/ 8 degree in two planes. More...

RD1078D741959 Glushko Lox/Kerosene rocket engine. 996 kN. Out of production. Diameter is per chamber. Isp=313s. Used on Vostok 8K72K launch vehicle. First flight 1960. More...

RD100 Glushko Lox/Alcohol rocket engine. 304 kN. R1, V1A. Isp=237s. Russian copy of the V2 engine using Russian materials  which made it very difficult! German rocket scientists assisted in its development. First flight 1948. More...

RD101 Glushko Lox/Alcohol rocket engine. 404 kN. R2 and V2A. Isp=237s. Developed simultaneously with the RD100 but with no German involvement. More compact, increased thrust, increased chamber pressure and higher alcohol concentration. First flight 1949. More...

RD102 Glushko Lox/Alcohol rocket engine. 428 kN. R3A. Development ended 1951. Project for R3A experimental missile. Stopped in favor of RD103. Isp=235s. More...

RD103 Glushko Lox/Alcohol rocket engine. 500 kN. R5. Out of Production. Isp=243s. Final extrapolation of the V2 rocket engine in Russia. First flight 1953. More...

RD103M Glushko Lox/Alcohol rocket engine. 500.1 kN. R5M 8K51. Isp=248s. First flight 1953. More...

RD103RD Glushko Lox/Alcohol rocket engine. M5RD. Out of Production. More...

RD105 Glushko Lox/Kerosene rocket engine. 627.6 kN. R7 ICBM stage 1 (strapon) initial project. Out of Production. Isp=302s. Single chamber engine intended for the R7 strapons in mid1950s. Subsequently replaced by the 4 chamber RD107. More...

RD106 Glushko Lox/Kerosene rocket engine. 645.3 kN. R7 ICBM stage 2 (core) initial project. Out of Production. Isp=310s. Single chamber engine intended for the R7 sustainer. Version of RD105 with larger nozzle. Subsequently replaced by the 4 chamber RD108. More...

RD118 Glushko Lox/Kerosene rocket engine. 999.601 kN. In production. Isp=311s. Update of RD107, used in Soyuz ST launcher. Little performance change from RD107, changes may mainly relate to use of allRussian components. First flight 2001. More...

RD10711D511P Glushko Lox/Kerosene rocket engine. 996.4 kN. Soyuz 11A511U20. Out of production. OKB Glushko. Used on 11A511U2 Stage 0. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=314s. First flight 1982. More...

RD1078D728 Glushko Lox/Kerosene rocket engine. 996 kN. Molniya 0, Molniya 8K78M0. OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG1 or T1) / Lox. Diameter is per chamber. Isp=314s. First flight 1964. More...

RD1078D741958 Glushko Lox/Kerosene rocket engine. 996 kN. Luna 8K720. Out of production. Diameter is per chamber. Isp=312s. First flight 1958. More...

RD1078D74K Glushko Lox/Kerosene rocket engine. 996 kN. Developed in 19571960. Used in strapons for Molniya 8K78, R7A 8K74, Voskhod 11A57, Vostok 8A92, Vostok 8A92M. Isp=313s. Fuel T1 or RG1 kerosene. First flight 1959. More...

RD1078D74PS Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8K71PS0. Out of Production. OKB Glushko. Used on 8K71PS Stage 0. Developed in 19561957. Flown 19571958. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=306s. More...

RD1088D75PS Glushko Lox/Kerosene rocket engine. 912 kN. Sputnik 8K71PS1. Out of Production. Diameter is per chamber. Isp=308s. First flight 1957. More...

RD117PF Glushko Lox/Kerosene rocket engine. manned Soyuzlauncher stage 1. Design concept. Update of RD107. Probably version using Sintin instead of kerosene. More...

RD117 Glushko Lox/Kerosene rocket engine. 1021.097 kN. Soyuz ST stage 1. In production. Update of RD107. Little performance change from RD107, changes may mainly relate to use of allRussian components. Isp=310s. First flown 2001. More...

RD111 Glushko Lox/Kerosene rocket engine. 1628 kN. R9 stage 1. Isp=317s. Developed for R9 ICBM. It had special flexible pipelines and gimbals, allowing lox loading in 20 minutes. First flight 1961. More...

RD1078D74 Glushko Lox/Kerosene rocket engine. 971 kN. R7 8K71, Vostok 8K72, Vostok 8K72K strapons. Isp=306s. First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's. More...

RD1088D77 Glushko Lox/Kerosene rocket engine. 804 kN. Sputnik 8A911. Out of Production. Diameter is per chamber. Isp=315s. First flight 1958. More...

RD1078D76 Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8A910. Out of Production. OKB Glushko. Used on 8A91 Stage 0. Developed in 19561957. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=310s. First flight 1958. More...

RD1088D75K Glushko Lox/Kerosene rocket engine. 941 kN. Molniya 8K781, R7A 8K741, Voskhod 11A571, Vostok 8A921, Vostok 8A92M1. Diameter is per chamber. Isp=315s. First flight 1959. More...

RD1088D751959 Glushko Lox/Kerosene rocket engine. 941 kN. Out of production. Further development of 8D741958, 19581959. Diameter is per chamber. Isp=315s. Used on Vostok 8K72K launch vehicle. First flight 1960. More...

RD1088D751958 Glushko Lox/Kerosene rocket engine. 941 kN. Luna 8K721. Out of production. Diameter is per chamber. Isp=315s. First flight 1958. More...

RD1088D75 Glushko Lox/Kerosene rocket engine. 912 kN. R7 8K711, Vostok 8K721, Vostok 8K72K1. OKB Glushko. Used on 8K71 R7 Stage 1. Developed in 19541955. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=308s. First flight 1957. More...

RD1088D727K Glushko Lox/Kerosene rocket engine. 976 kN. Molniya 8K783. Out of Production. Isp=316s. More...

RD1088D727 Glushko Lox/Kerosene rocket engine. 977 kN. Molniya 1, Molniya 8K78M1. OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG1 or T1) / Lox. Diameter is per chamber. Isp=316s. First flight 1964. More...

RD10811D512P Glushko Lox/Kerosene rocket engine. 1011 kN. Soyuz 11A511U21. Out of production. Isp=319s. A 12 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. First flight 1982. More...

RD10811D512 Glushko Lox/Kerosene rocket engine. 997 kN. Soyuz 11A5111, Soyuz 11A511U1. Design 2000. Diameter is per chamber. Isp=315s. First flight 1965. More...

RD110 Glushko Lox/Kerosene rocket engine. 1374 kN. Development ended 1949. Isp=285s. For R3 IRBM, 19 ED140 7 tonne chambers used as preburners to feed a main mixing chamber, a scaleup of the V2 production motor. Tested, but technical problems too severe. More...

RD3A Glushko Lox/Alcohol rocket engine. R3A. Out of Production. Project for R3A experimental missile. Stopped in favour of RD103. More...

RD58Z Korolev Lox/Kerosene rocket engine. 71 kN. Zenit stage 3. Developed 19811990. Isp=361s. More...

RD56M LNG Isayev Lox/LNG rocket engine. 73.5 kN. Vozdushnyy Start stage 2. Developed 1996. Variant of RD56M using liquid natural gas in place of hydrogen. First engine tests performed in 1998. More...

RD58 Korolev Lox/Kerosene rocket engine. 83.4 kN. Isp=349s. Highperformance upperstage engine developed for N1 lunar crasher stage, but saw general use as restartable Block D upper stage of Proton launch vehicle. First flight 1967. More...

RD58M Korolev Lox/Kerosene rocket engine. 83.4 kN. Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM). In production. Isp=353s. First flight 1974. More...

RD58MF Korolev Lox/Kerosene rocket engine. 83.4 kN. In Production. Isp=353s. Multifunction variant of RD58 for uprated upper stages applications (Zenit stage 3, Angara). BlockDMSL for SeaLaunch may have used RD58M. More...

RD58S Korolev Lox/Kerosene rocket engine. 86.3 kN. Proton 8K82K / 11S86101 stage 4 (block DM). Version 17D12 for Buran OMS. Version uses synthetic kerosene ('Sintin') for higher specific impulse. Isp=361s. First flight 1994. More...

RD809 Yuzhnoye Lox/Kerosene rocket engine. 88 kN. Upper stages. Isp=345s. 2007 design concept for a fourchamber restartable main engine for launch vehicle upper stages. More...

RD802 Yuzhnoye Lox/Kerosene rocket engine. 19.6 kN. Upper stages. Design concept 2007. Isp=344s. Derivative of the RD8 Zenit2 second stage vernier thrust engine combustion chamber for use in launch vehicle upper stages. More...

RD8 Yuzhnoye Lox/Kerosene rocket engine. 78.4 kN. Zenit stage 2 attitude control engine. In Production. Isp=342s. Fourchamber pumpfed singlerun engine operated in a staged combustion scheme with afterburning of the generator gas. Development began in 1976. More...

RDKS100 Dushkin Lox/Kerosene rocket engine. 980 kN. Sanger. Developed 194651. Isp=285s. More...

RDMT200K NII Mash GOX/Kerosene rocket engine. 0.200 kN. Buran. Out of Production. Lowthrust attitude control thruster. Mass in ref. NIIMash 95 given as only 2.5 kg. Isp=265s. More...

RDMT2600 NII Mash GOX/Alcohol rocket engine. 2.6 kN. Developed 1980's. Experimental lowthrust thruster. Isp=270s. More...

RKDS100 Glushko Lox/Kerosene rocket engine. 980 kN. Keldysh Bomber. Design 1946. Nominal design engine for 1946 Keldysh bomber design. The Soviet Union would not produce an engine with these propellants and thrust levels until nearly 20 years later. Isp=285s. More...

RLA300 Glushko Lox/Kerosene rocket engine. 3187 kN. Design 1974. Proposed for the RLA series launch vehicles and the UR700M Mars booster. Following rejection of RLA, design 'downsized' to 200 tonnes thrust for Energia and Zenit. More...

RLA600 Glushko Lox/Kerosene rocket engine. 6370 kN. Design 1972. Twochamber version of RLA300. Proposed for the RLA series launch vehicles and the UR700M Mars booster. More...

RLA1200 Glushko Lox/Kerosene rocket engine. 12,700 kN. Design 1974. Proposed engines for the RLA series launch vehicles. This version would use four chambers. 'Downsized' to 200 tonnes thrust for Energia. More...

Rotary Rocket XCOR Lox/Kerosene rocket engine. 22.250 kN. First stages. Developed in 1990's. Developed and tested by Rotary Rocket for their launcher before its cancellation. More...

RPD04 Dushkin Lox/Kerosene rocket engine. Out of Production. More...

RS27 Rocketdyne Lox/Kerosene rocket engine. 1023 kN. Out of production. Isp=295s. Consisted of RS2701A/B main engine, and twin LR101NA11 verniers. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher; replaced the MB3. First flight 1972. More...

RS27A Rocketdyne Lox/Kerosene rocket engine. 1054.2 kN. . Isp=302s. Replaced the RS27 as the main system for the Delta and in the MA 5A for the Atlas. RS2701B main engine, and twin LR101NA11 verniers. First flight 1989. More...

RS27C Rocketdyne Lox/Kerosene rocket engine for Delta 7000. 1054.2 kN. Isp=302s. First flight 1990. More...

RS34 Attitude Control Rocketdyne Lox/Kerosene rocket engine. 0.304 kN. Peacekeeper Postboost Attitude Control. Pressurefed. 8 attitude thrusters in each postboost propulsion system. Isp=255s. First flight 1983. More...

RS36 Sustainer Rocketdyne Lox/Kerosene rocket engine. 9.210 kN. HOE Homing Overlay Experiment Upper Stage Axial Propulsion System. Pressurefed. Derivative of Lance propulsioon system. Isp=262s. First flight 1983. More...

RS56OSA Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Out of production. Designed for booster applications. Gas generator, pumpfed. Isp=316s. Sustainer engine for Atlas II, IIA, IIAS. First flight 1991. More...

RS56OBA Rocketdyne Lox/Kerosene rocket engine. 1046.8 kN. Out of production. Designed for booster applications. Gas generator, pumpfed. Isp=299s. Booster engine for Atlas II, IIA, IIAS. First flight 1991. More...

RS76 Rocketdyne Lox/Kerosene rocket engine. Launch thrust 4002 kN. Space Shuttle Reusable First Stage. OxRich staged combustion, pumpfed. Thrust and specific impulse values are at sea level. More...

RS84 Rocketdyne lox/kerosene rocket engine. 5159 kN. Booster stages. Development ended 2005. Isp=335s. Design for NASA's Space Launch Initiative; borrowed extensively from Russian technology developed in the forty years since the USA abandoned the F1. More...

RSX Rocketdyne Lox/Kerosene rocket engine. 1890 kN. Design concept 1997. Employed existing Delta and Atlas MA and RS engine hardware with a new thrust chamber assembly to generate a thrust of 1890 kN for ELV applications. More...

RZ.2 Rolls Royce Lox/Kerosene rocket engine. 836.3 kN. Isp=282s. Used on Europa launch vehicle. First flight 1964. More...

S3 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Juno II, Saturn A2 studies of 1959. Isp=282s. First flight 1958. More...

S3D Rocketdyne Lox/Kerosene rocket engine. Launch thrust 600.1 kN. Jupiter Booster. Gas generator, pumpfed. Thrust later 150,000 lbs. Thrust and specific impulse values are at sea level. First flight 1957. More...

S4 Rocketdyne Lox/Kerosene rocket engine. 412.8 kN. Design ca. 1957. Version of Atlas sustainer tailored to Redstone Arsenal upperstage requirements. Paper study only. Used on Super Jupiter launch vehicle. More...

S1.35800 Korolev Lox/Kerosene rocket engine. 30 kN. R7 verniers. Out of Production. Thrust variable 2.53.1 tf More...

S1.5400A Korolev Lox/Kerosene rocket engine. 67.3 kN. Molniya 8K78M3. Isp=342s. First flight 1964. More...

S1.5400 Korolev Lox/Kerosene rocket engine. 66.7 kN for Molniya 8K78 Stage 3. Flew 19601965. Isp=340s. Designed by Korolev; passed to Isayev for production. Began a series of engines leading through the 8D726 for GR1 to the Block D for the N1 and Proton. More...

S2.253 derivative Isayev Lox/Kerosene rocket engine. 93.2 kN. EKR (experimental winged missile). Study 1953. Derivative of S2.253 was proposed for use in EKR Stage 1 (project for an experimental winged missile). Isp=250s. More...

S5.80.11000 Isayev Lox/Kerosene rocket engine. 2.940 kN. Soyuz2 Blok LM. Developed 1990s. Thrust chamber from KTDU80 / S5.80 converted to burn Lox/Kerosene. More...

SangerBredt Notional Lox/Kerosene rocket engine. 1428.8 kN. Study 1943. Used in SangerBredt. Isp=306s. More...

SangerBredt Sled Saenger Lox/Alcohol rocket engine. 1144.1 kN. Study 1943. Isp=245s. Used on Sanger launch vehicle. More...

Sea Dragon1 Aerojet Lox/Kerosene rocket engine. 356,9 kN. Design, 1962. Isp=290s. Truax pressure fed design. Thrust, chamber pressure varied during ascent. More...

Sled Technology Rocketdyne Lox/Alcohol rocket engine. 666 kN. Pressurefed. From 35,000 to 150,000 lbf. Cook Sled, Air Force Sleds 1 and 2, RS2 Sled, operated at Edwards and Holloman Air Force Bases. More...

TR107 TRW lox/kerosene rocket engine. 4900 kN. Booster stages. TRW design for NASA's Space Launch Initiative. The engine used ductcooling of the main combustion chamber and materials that would not interact with kerosene to minimise coking. More...

X1 Rocketdyne Lox/Kerosene rocket engine. 880.440 kN. Booster applications. Gas generator, pumpfed. Thrust from 165,000 to 198,000 lbs. More...

X405 GE Lox/Kerosene rocket engine. 134.8 kN. Vanguard 1st stage. Isp=270s. First flight 1957. More...

XLR1055 Rocketdyne Lox/Kerosene rocket engine. 363.2 kN. Atlas D. Atlas Sustainer. Gas generator, pumpfed. Shared turbopumps for booster engines. Isp=309s. First flight 1958. More...

XLR11 Reaction Motors, Thiokol Lox/Alcohol rocket engine. Out of Production. Launch thrust 26.67 kN. Rocket engine developed for X1 in 1940s to break the sound barrier and used twenty years later to power experimental lifting bodies. Four combustion chambers. More...

XLR25CW1 CurtissWright Lox/Alcohol rocket engine. 66.880 kN. Out of Production. First flight 1954. Two chamber engine built for X2 rocketplane. Engine could be throttled continuously from 1140 kgf to 6820 kgf. More...

XLR43NA1 Rocketdyne Lox/Alcohol rocket engine. 333 kN. Development completed 1951. Mark III American version of singlechamber V2 engine tested in WW2, but with half mass and 34% more thrust. Starting point for all later Rocketdyne engines. More...

XLR71NA1 Rocketdyne Lox/Alcohol rocket engine. Development cancelled 1955. Launch thrust 533.7 kN. Planned engine for the booster of the Navaho II test vehicle. Gas generator, pumpfed. More...

XLR83NA1 Rocketdyne Lox/Kerosene rocket engine. 602 kN. Out of production. Isp=273s. Experimental version of the engine for the booster of the Navaho G38 intercontinental cruise missile. Flown in the Navaho G26 booster prototypes. First flight 1956. More...

XLR891 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Atlas A, B, C. Out of production. Designed for booster applications. Gas generator, pumpfed. Shared turbopumps for booster engines. Isp=282s. First flight 1957. More...

XLR895 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Atlas D. Designed for booster applications. Gas generator, pumpfed. Shared turbopumps for booster engines. Isp=282s. First flight 1958. More...

XLR99 Thiokol Lox/Ammonia rocket engine. 262.4 kN. Out of production. Isp=276s. The first large, manrated, throttleable, restartable liquid propellant rocket engine, boosted the X15A. First flight 1959. More...

XR2P1 XCOR Nitrous oxide/Alcohol rocket engine. 0.067 kN. First stages. Hardware. Engine was run on oxygen and nitrous oxide oxidizers, with propane, ethane, kerosene, turpentine, and a variety of alcohols. More...

XR3A2 XCOR Lox/Alcohol rocket engine. 0.700 kN. First stages. Hardware. The XR3A2 700newton engine was the first XCOR LOX/alcohol engine, accumulating 61 brief runs in the course of injector concept development, which led to later engines. More...

XR3B4 XCOR Nitrous oxide/Alcohol rocket engine. 0.220 kN. First stages. Hardware. Regeneratively cooled engine using nitrous oxide and isopropyl alcohol as propellants. More...

XR3M9 XCOR Lox/CH4 rocket engine. 0.223 kN. First stages. Hardware. Methanefueled engine allowing longterm onorbit storage, higher density than hydrogen engines. Intended for use in reaction control systems and satellite maneuvering systems More...

XR4A3 XCOR Lox/Alcohol rocket engine. 1.780 kN. First stages. Fully operational pressurefed, regeneratively cooled engine. Flown on the EZRocket, a modified LongEZ aircraft fitted with two engines. First flight 2001. More...

XR4K14 XCOR Lox/Kerosene rocket engine. 6.670 kN. First stages. Hardware. Built for the Rocket Racing League's first XRacer. The rocket engine was sized for the best compromise between acceleration and endurance. More...

XR4K5 XCOR Lox/Kerosene rocket engine. 8 kN. First stages. Hardware. Pumpfed, regeneratively cooled with fuel. Engine could be used to power the prototype Xerus suborbital manned vehicle for initial flight testing. More...

XR5M12 XCOR Lox/CH4 rocket engine. 22.3 kN. First stages. Conceptual lox/methane rocket engine developed for a DARPA program through layout design phase, but never built. More...

XR5M15 XCOR Lox/CH4 rocket engine. 33.360 kN. First stages. Hardware. Prototype LOX/methane rocket engine developed as a stepping stone to NASA's original Orion manned spacecraft and return to the moon and manned mission to Mars plans. More...

YF120t CAALPT Lox/Kerosene rocket engine. 1340.2 kN. In development. Isp=336s. For CZ5 Next Generation Launch Vehicle series. Engine can be throttled to 65% of rated thrust. Firing tests began in 2005. More...
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