The highestspecific impulse chemical rockets use liquid propellants (liquid-propellant rockets). They can consist of a single chemical (amonopropellant) or a mix of two chemicals, calledbipropellants. Bipropellants can further be divided into two categories;hypergolic propellants, which ignite when the fuel andoxidizer make contact, and non-hypergolic propellants which require an ignition source.^[1]

About 170 differentpropellants made ofliquid fuel have been tested, excluding minor changes to a specific propellant such as propellant additives, corrosion inhibitors, or stabilizers. In the U.S. alone at least 25 different propellant combinations have been flown.^[2]

Many factors go into choosing a propellant for a liquid-propellant rocket engine. The primary factors include ease of operation, cost, hazards/environment and performance.^{[citation needed]}

Konstantin Tsiolkovsky proposed the use of liquid propellants in 1903, in his articleExploration of Outer Space by Means of Rocket Devices.^[3][4]

On March 16, 1926,Robert H. Goddard usedliquid oxygen (LOX) andgasoline aspropellants for his first partially successfulliquid-propellant rocket launch. Both propellants are readily available, cheap and highly energetic. Oxygen is a moderatecryogen as air will not liquefy against a liquid oxygen tank, so it is possible to store LOX briefly in a rocket without excessive insulation.^{[clarification needed]}

In Germany, engineers and scientists began building and testing liquid propulsion rockets in the late 1920s.^[5] According toMax Valier, two liquid-propellantOpel RAK rockets were launched inRüsselsheim on April 10 and April 12, 1929.^[6]

Germany had very active rocket development before and duringWorld War II, both for the strategicV-2 rocket and other missiles. The V-2 used an alcohol/LOXliquid-propellant engine, withhydrogen peroxide to drive the fuel pumps.^[7]: 9 The alcohol was mixed with water for engine cooling. Both Germany and the United States developed reusable liquid-propellant rocket engines that used a storeable liquid oxidizer with much greater density than LOX and a liquid fuel thatignited spontaneously on contact with the high density oxidizer.^{[citation needed]}

The major manufacturer of German rocket engines for military use, theHWK firm,^[8] manufactured theRLM-numbered109-500-designation series of rocket engine systems, and either usedhydrogen peroxide as a monopropellant forStarthilfe rocket-propulsive assisted takeoff needs;^[9] or as aform of thrust forMCLOS-guided air-sea glide bombs;^[10] and used in a bipropellant combination of the same oxidizer with afuel mixture of hydrazine hydrate and methyl alcohol forrocket engine systems intended for manned combat aircraft propulsion purposes.^[11]

The U.S. engine designs were fueled with the bipropellant combination ofnitric acid as the oxidizer; andaniline as the fuel. Both engines were used to power aircraft, theMe 163 Komet interceptor in the case of the Walter 509-series German engine designs, andRATO units from both nations (as with theStarthilfe system for the Luftwaffe) to assist take-off of aircraft, which comprised the primary purpose for the case of the U.S. liquid-fueled rocket engine technology - much of it coming from the mind of U.S. Navy officerRobert Truax.^[12]

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During the 1950s and 1960s there was a great burst of activity by propellant chemists to find high-energy liquid and solid propellants better suited to the military. Large strategic missiles need to sit in land-based or submarine-based silos for many years, able to launch at a moment's notice. Propellants requiring continuous refrigeration, which cause their rockets to grow ever-thicker blankets of ice, were not practical. As the military was willing to handle and use hazardous materials, a great number of dangerous chemicals were brewed up in large batches, most of which wound up being deemed unsuitable for operational systems.^{[citation needed]} In the case ofnitric acid, the acid itself (HNO
₃) was unstable, and corroded most metals, making it difficult to store. The addition of a modest amount ofnitrogen tetroxide,N
₂O
₄, turned the mixture red and kept it from changing composition, but left the problem that nitric acid corrodes containers it is placed in, releasing gases that can build up pressure in the process. The breakthrough was the addition of a littlehydrogen fluoride (HF), which forms a self-sealing metal fluoride on the interior of tank walls thatInhibited Red Fuming Nitric Acid. This made "IRFNA" storeable.

Propellant combinations based on IRFNA or pureN
₂O
₄ as oxidizer and kerosene orhypergolic (self igniting)aniline,hydrazine orunsymmetrical dimethylhydrazine (UDMH) as fuel were then adopted in the United States and the Soviet Union for use in strategic and tactical missiles. The self-igniting storeable liquid bi-propellants have somewhat lower specific impulse than LOX/kerosene but have higher density so a greater mass of propellant can be placed in the same sized tanks. Gasoline was replaced by differenthydrocarbon fuels,^[7] for exampleRP-1 – a highly refined grade ofkerosene. This combination is quite practical for rockets that need not be stored.

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The V-2 rockets developed by Nazi Germany used LOX and ethyl alcohol. One of the main advantages of alcohol was its water content, which provided cooling in larger rocket engines. Petroleum-based fuels offered more power than alcohol, but standard gasoline and kerosene left too much soot and combustion by-products that could clog engine plumbing. In addition, they lacked the cooling properties of ethyl alcohol.

During the early 1950s, the chemical industry in the US was assigned the task of formulating an improved petroleum-based rocket propellant which would not leave residue behind and also ensure that the engines would remain cool. The result wasRP-1, the specifications of which were finalized by 1954. A highly refined form of jet fuel, RP-1 burned much more cleanly than conventional petroleum fuels and also posed less of a danger to ground personnel from explosive vapours. It became the propellant for most of the early American rockets and ballistic missiles such as the Atlas, Titan I, and Thor. The Soviets quickly adopted RP-1 for their R-7 missile, but the majority of Soviet launch vehicles ultimately used storable hypergolic propellants. As of 2017^[update], it is used in thefirst stages of many orbital launchers.

Many early rocket theorists believed thathydrogen would be a marvelous propellant, since it gives the highestspecific impulse. It is also considered the cleanest when oxidized withoxygen because the only by-product is water. Steam reforming ofnatural gas is the most common method of producing commercial bulk hydrogen at about 95% of the world production^[13][14] of500 billion m³ in 1998.^[15] At high temperatures (700–1100 °C) and in the presence of ametal-basedcatalyst (nickel), steam reacts with methane to yieldcarbon monoxide and hydrogen.

Hydrogen is very bulky compared to other fuels; it is typically stored as a cryogenic liquid, a technique mastered in the early 1950s as part of thehydrogen bomb development program atLos Alamos.Liquid hydrogen can be stored and transported without boil-off, by usinghelium as a cooling refrigerant, since helium has an even lower boiling point than hydrogen. Hydrogen is lost via venting to the atmosphere only after it is loaded onto a launch vehicle, where there is no refrigeration.^[16]

In the late 1950s and early 1960s it was adopted for hydrogen-fuelled stages such asCentaur andSaturn upper stages.^{[citation needed]} Hydrogen has low density even as a liquid, requiring large tanks and pumps; maintaining the necessary extreme cold requires tank insulation. This extra weight reduces the mass fraction of the stage or requires extraordinary measures such as pressure stabilization of the tanks to reduce weight. (Pressure stabilized tanks support most of the loads with internal pressure rather than with solid structures, employing primarily thetensile strength of the tank material.^{[citation needed]})

The Soviet rocket programme, in part due to a lack of technical capability, did not use liquid hydrogen as a propellant until theEnergia core stage in the 1980s.^{[citation needed]}

The liquid-rocket engine bipropellantliquid oxygen and hydrogen offers the highest specific impulse for conventional rockets. This extra performance largely offsets the disadvantage of low density, which requires larger fuel tanks. However, a small increase in specific impulse in an upper stage application can give a significant increase in payload-to-orbit mass.^[17]

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Launch pad fires due to spilled kerosene are more damaging than hydrogen fires, for two main reasons:

• Kerosene burns about 20% hotter in absolute temperature than hydrogen.
• Hydrogen's buoyancy. Since hydrogen is a deep cryogen it boils quickly and rises, due to its very low density as a gas. Even when hydrogen burns, thegaseousH
  ₂O that is formed has a molecular weight of only 18 AMU compared to 29.9 AMU for air, so it also rises quickly. Spilled kerosene fuel, on the other hand, falls to the ground and if ignited can burn for hours when spilled in large quantities.

Kerosene fires unavoidably cause extensive heat damage that requires time-consuming repairs and rebuilding. This is most frequently experienced by test stand crews involved with firings of large, unproven rocket engines.

Hydrogen-fuelled engines require special design, such as running propellant lines horizontally, so that no "traps" form in the lines, which would cause pipe ruptures due to boiling in confined spaces. (The same caution applies to other cryogens such as liquid oxygen andliquid natural gas (LNG).) Liquid hydrogen fuel has an excellent safety record and performance that is well above all other practical chemical rocket propellants.

The highest-specific-impulse chemistry ever test-fired in a rocket engine waslithium andfluorine, with hydrogen added to improve the exhaust thermodynamics (all propellants had to be kept in their own tanks, making this atripropellant). The combination delivered 542 s specific impulse in vacuum, equivalent to an exhaust velocity of 5320 m/s. The impracticality of this chemistry highlights why exotic propellants are not actually used: to make all three components liquids, the hydrogen must be kept below −252 °C (just 21 K), and the lithium must be kept above 180 °C (453 K). Lithium and fluorine are both extremely corrosive. Lithium ignites on contact with air, and fluorine ignites most fuels on contact, including hydrogen. Fluorine and thehydrogen fluoride (HF) in the exhaust are very toxic, which makes working around the launch pad difficult, damages the environment, and makes getting alaunch license more difficult. Both lithium and fluorine are expensive compared to most rocket propellants. This combination has therefore never flown.^[18]

During the 1950s, the Department of Defense proposed lithium/fluorine as ballistic-missile propellants. A 1954 accident at a chemical works that released a cloud of fluorine into the atmosphere convinced them to use LOX/RP-1 instead.^{[citation needed]}

Using liquid methane and liquid oxygen as propellants is sometimes called methalox propulsion.^[19]Liquidmethane has a lower specific impulse than liquid hydrogen, but is easier to store due to its higher boiling point and density, as well as its lack ofhydrogen embrittlement. It also leaves less residue in the engines compared to kerosene, which is beneficial for reusability.^[20][21] In addition, it is expected that its production on Mars will be possible via theSabatier reaction. In NASA'sMars Design Reference Mission 5.0 documents (between 2009 and 2012),liquid methane/LOX (methalox) was the chosen propellant mixture for the lander module.

Due to the advantages methane fuel offers, some private space launch providers aimed to develop methane-based launch systems during the 2010s and 2020s. The competition between countries was dubbed the Methalox Race to Orbit, with theLandSpace'sZhuque-2 methalox rocket becoming the first to reach orbit.^[22][23][24]

As of January 2025^[update], three methane-fueled rockets have reached orbit. Several others are in development and two orbital launch attempts failed:

• Zhuque-2 successfully reached orbit on its second flight on 12 July 2023, becoming the first methane-fueled rocket to do so.^[25] It had failed to reach orbit on its maiden flight on 14 December 2022. The rocket, developed byLandSpace, uses theTQ-12 andTQ-11 orTQ-15A engines.
• Vulcan Centaur successfully reached orbit on its first try, called Cert-1, on 8 January 2024.^[26] The rocket, developed byUnited Launch Alliance, uses theBlue Origin'sBE-4 engine, though the second stage uses the hydroloxRL10.
• New Glenn successfully reached orbit on its first try on 16 January 2025. The rocket and its engines are developed by Blue Origin. The first stage uses BE-4 engines, and the second stage uses the hydroloxBE-3U.
• Terran 1 had a failed orbital launch attempt on its maiden flight on 22 March 2023, and the development of the rocket was terminated. The rocket, developed byRelativity Space, uses theAeon 1 engine.
• Starship achieved atransatmospheric orbit on itsthird flight on 14 March 2024,^[27] after two failed attempts. The rocket, developed bySpaceX, uses theRaptor engine.
• Nova is being developed byStoke Space. The first stage uses methalox Zenith engine, and the second stage uses a hydrolox engine.

SpaceX developed theRaptor engine for its Starship super-heavy-lift launch vehicle.^[28] It has been used intest flights since 2019. SpaceX had previously used onlyRP-1/LOX and hypergolics in their engines.

Blue Origin developed the BE-4 LOX/LNG engine for theirNew Glenn and the United Launch Alliance Vulcan Centaur. The BE-4 provides 2,400 kN (550,000 lbf) of thrust. Two flight engines had been delivered to ULA by mid 2023.

ESA is developing a 980kN methaloxPrometheus rocket engine which was test fired in 2023.^[29]

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High-test peroxide

High test peroxide is concentratedHydrogen peroxide, with around 2% to 30% water. It decomposes to steam and oxygen when passed over a catalyst. This was historically used for reaction control systems, due to being easily storable. It is often used to driveTurbopumps, being used on theV2 rocket, and modernSoyuz.

Hydrazine

decomposes energetically to nitrogen, hydrogen, and ammonia (2N₂H₄ → N₂+H₂+2NH₃) and is the most widely used in space vehicles. (Non-oxidized ammonia decomposition is endothermic and would decrease performance).

Nitrous oxide

decomposes to nitrogen and oxygen.

Steam

when externally heated gives a reasonably modest I_sp of up to 190 seconds, depending on material corrosion and thermal limits.

As of March 2025^[update], liquid fuel combinations in common use:

Kerosene (RP-1) /liquid oxygen (LOX)

Used for the lower stages of theSoyuz-2,Angara A5,Long March 6,Long March 7,Long March 8, andTianlong-2; boosters ofLong March 5; the first stage ofAtlas V; both stages ofElectron,Falcon 9,Falcon Heavy,Firefly Alpha,Long March 12, andAngara-1.2; and all three stages ofNuri.

Liquid hydrogen (LH) / LOX

Used in the stages of theSpace Launch System,New Shepard,H3,GSLV,LVM3,Long March 5,Long March 7A,Long March 8,Ariane 6,New Glenn andCentaur.

Liquid methane (LNG) / LOX

Used in both stages ofZhuque-2,Starship (doing nearly orbital test flights), and the first stage of theVulcan Centaur and New Glenn.

Unsymmetrical dimethylhydrazine (UDMH) ormonomethylhydrazine (MMH) /dinitrogen tetroxide (NTO orN
₂O
₄)

Used in three first stages of the RussianProton booster, IndianVikas engine forPSLV,GSLV, and LVM3 rockets, many Chinese boosters, a number of military, orbital and deep space rockets, as this fuel combination ishypergolic and storable for long periods at reasonable temperatures and pressures.

Hydrazine (N
₂H
₄)

Used in deep space missions because it isstorable and hypergolic, and can be used as a monopropellant with a catalyst.

Aerozine-50 (50/50 hydrazine and UDMH)

Used in deep space missions because it isstorable and hypergolic, and can be used as a monopropellant with a catalyst.

The table uses data from the JANNAF thermochemical tables (Joint Army-Navy-NASA-Air Force (JANNAF) Interagency Propulsion Committee) throughout, with best-possible specific impulse calculated by Rocketdyne under the assumptions ofadiabatic combustion,isentropic expansion, one-dimensional expansion and shifting equilibrium.^[30] Some units have been converted to metric, but pressures have not.

V_e

Average exhaust velocity, m/s. The same measure as specific impulse in different units, numerically equal to specific impulse in N·s/kg.

r

Mixture ratio: mass oxidizer / mass fuel

T_c

Chamber temperature, °C

d

Bulk density of fuel and oxidizer, g/cm³

C*

Characteristic velocity, m/s. Equal to chamber pressure multiplied by throat area, divided bymass flow rate. Used to check experimental rocket'scombustion efficiency.

Definitions of some of the mixtures:

IRFNA IIIa

83.4%HNO₃, 14%NO₂, 2%H₂O, 0.6%HF

IRFNA IV HDA

54.3% HNO₃, 44% NO₂, 1% H₂O, 0.7% HF

RP-1

See MIL-P-25576C, basically kerosene (approximatelyC
₁₀H
₁₈)

MMHmonomethylhydrazine

CH
₃NHNH
₂

Has not all data for CO/O₂, purposed for NASA for Martian-based rockets, only a specific impulse about 250 s.

r

Mixture ratio: mass oxidizer / mass fuel

V_e

Average exhaust velocity, m/s. The same measure as specific impulse in different units, numerically equal to specific impulse in N·s/kg.

C*

Characteristic velocity, m/s. Equal to chamber pressure multiplied by throat area, divided bymass flow rate. Used to check experimental rocket's combustion efficiency.

T_c

Chamber temperature, °C

d

Bulk density of fuel and oxidizer, g/cm³

• Cpropep-Web an online computer program to calculate propellant performance in rocket engines
• Design Tool for Liquid Rocket Engine Thermodynamic Analysis is a computer program to predict the performance of the liquid-propellant rocket engines.

• Rocket propulsion
• Rocket propellants

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