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Comparison of orbital rocket engines. 6 languages. ... This page is an incomplete list of orbital rocket engine data and specifications. Current, upcoming, and in ...
Compared to other types of jet engine, rocket engines are the lightest and have the highest thrust, but are the least propellant-efficient (they have the lowest specific impulse). The ideal exhaust is hydrogen, the lightest of all elements, but chemical rockets produce a mix of heavier species, reducing the exhaust velocity.
Unlike ducted engines, rockets give thrust even when the two speeds are equal. In 1903, Konstantin Tsiolkovsky discussed the average propulsive efficiency of a rocket, which he called the utilization (utilizatsiya), the "portion of the total work of the explosive material transferred to the rocket" as opposed to the exhaust gas. [6]
The higher the specific impulse, the better the efficiency. Ion propulsion engines have high specific impulse (~3000 s) and low thrust [19] whereas chemical rockets like monopropellant or bipropellant rocket engines have a low specific impulse (~300 s) but high thrust. [20]
This comparison of orbital launch systems lists the attributes of all current and future individual rocket configurations designed to reach orbit. A first list contains rockets that are operational or have attempted an orbital flight attempt as of 2024; a second list includes all upcoming rockets.
Hence effective exhaust velocity is not physically meaningful for air-breathing engines; nevertheless, it is useful for comparison with other types of engines. [39] The highest specific impulse for a chemical propellant ever test-fired in a rocket engine was 542 seconds (5.32 km/s) with a tripropellant of lithium, fluorine, and hydrogen ...
These engines would use staged cycle combustion, for higher efficiency similar to the system used on the former Soviet Union's NK-33 engine. [2] [needs update] By mid-2015, SpaceX had developed a total of 9 rocket engines architectures in the first 13 years of the company's existence. [3]
Characteristic velocity or , or C-star is a measure of the combustion performance of a rocket engine independent of nozzle performance, and is used to compare different propellants and propulsion systems. c* should not be confused with c, which is the effective exhaust velocity related to the specific impulse by: =. Specific impulse and ...
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