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  2. Nozzle - Wikipedia

    en.wikipedia.org/wiki/Nozzle

    A gas jet, fluid jet, or hydro jet is a nozzle intended to eject gas or fluid in a coherent stream into a surrounding medium. Gas jets are commonly found in gas stoves , ovens , or barbecues . Gas jets were commonly used for light before the development of electric light .

  3. Propane, butane, and LPG container valve connections

    en.wikipedia.org/wiki/Propane,_butane,_and_LPG...

    The iOverlander [2] database maintained by travelers, My LPG [3] and the Facebook group "Cooking Gas Around the World [4]" provide more information about individual sources per country. Much general information about global LPG use and standardization is available from the World LPG Association [ 5 ] and the AEGPL [ 6 ]

  4. Isentropic nozzle flow - Wikipedia

    en.wikipedia.org/wiki/Isentropic_Nozzle_Flow

    is the density of the gas (kg/m 3) is the temperature of the gas (K) is the cross sectional area of the nozzle at the point of interest (m 2) is the cross sectional area of the nozzle at the sonic point, or the point where gas velocity is Mach 1 (m 2). Ideally this will occur at the nozzle throat.

  5. Gasoline pump - Wikipedia

    en.wikipedia.org/wiki/Gasoline_pump

    A gasoline pump or fuel dispenser is a machine at a filling station that is used to pump gasoline (petrol), diesel, or other types of liquid fuel into vehicles. Gasoline pumps are also known as bowsers or petrol bowsers (in Australia and South Africa ), [ 2 ] [ 3 ] petrol pumps (in Commonwealth countries), or gas pumps (in North America ).

  6. Propelling nozzle - Wikipedia

    en.wikipedia.org/wiki/Propelling_nozzle

    Beyond this point the nozzle diameter becomes the biggest diameter and starts to incur increasing drag. Nozzles are thus limited to the installation size and the loss in thrust incurred is a trade off with other considerations such as lower drag, less weight. Examples are the F-16 at Mach 2.0 [21] and the XB-70 at Mach 3.0. [22]

  7. Rocket engine nozzle - Wikipedia

    en.wikipedia.org/wiki/Rocket_engine_nozzle

    The gas flow rate is constant (i.e., steady) during the period of the propellant burn. The gas flow is non-turbulent and axisymmetric from gas inlet to exhaust gas exit (i.e., along the nozzle's axis of symmetry). The flow is compressible as the fluid is a gas. As the combustion gas enters the rocket nozzle, it is traveling at subsonic velocities.

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