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  2. Pintle injector - Wikipedia

    en.wikipedia.org/wiki/Pintle_injector

    Fuel in red, oxidizer in blue. The pintle injector is a type of propellant injector for a bipropellant rocket engine.Like any other injector, its purpose is to ensure appropriate flow rate and intermixing of the propellants as they are forcibly injected under high pressure into the combustion chamber, so that an efficient and controlled combustion process can happen.

  3. Rocket engine nozzle - Wikipedia

    en.wikipedia.org/wiki/Rocket_engine_nozzle

    A rocket engine nozzle is a propelling nozzle (usually of the de Laval type) ... The central throat is of a standard design and is surrounded by an annular throat ...

  4. Rocket engine - Wikipedia

    en.wikipedia.org/wiki/Rocket_engine

    RS-68 being tested at NASA's Stennis Space Center Viking 5C rocket engine used on Ariane 1 through Ariane 4. A rocket engine is a reaction engine, producing thrust in accordance with Newton's third law by ejecting reaction mass rearward, usually a high-speed jet of high-temperature gas produced by the combustion of rocket propellants stored inside the rocket.

  5. de Laval nozzle - Wikipedia

    en.wikipedia.org/wiki/De_Laval_nozzle

    Diagram of a de Laval nozzle, showing approximate flow velocity (v), together with the effect on temperature (T) and pressure (p) A de Laval nozzle (or convergent-divergent nozzle, CD nozzle or con-di nozzle) is a tube which is pinched in the middle, with a rapid convergence and gradual divergence.

  6. Propelling nozzle - Wikipedia

    en.wikipedia.org/wiki/Propelling_nozzle

    When afterburning engines are equipped with a C-D nozzle the throat area is variable. Nozzles for supersonic flight speeds, at which high nozzle pressure ratios are generated, [2] also have variable area divergent sections. [3] Turbofan engines may have an additional and separate propelling nozzle which further accelerates the bypass air.

  7. RL10 - Wikipedia

    en.wikipedia.org/wiki/RL10

    The expander cycle that the engine uses drives the turbopump with waste heat absorbed by the engine combustion chamber, throat, and nozzle. This, combined with the hydrogen fuel, leads to very high specific impulses ( I sp ) in the range of 373 to 470 s (3.66–4.61 km/s) in a vacuum.

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    mail.aol.com

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  9. RD-843 - Wikipedia

    en.wikipedia.org/wiki/RD-843

    The RD-843 is a Ukrainian single nozzle liquid propellant rocket engine. It burns a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide (N 2 O 4) oxidizer. It is pressure-fed. It is rated for up to 5 restarts, and can gimbal up to 10 degrees in each direction. [2]