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  2. Choked flow - Wikipedia

    en.wikipedia.org/wiki/Choked_flow

    where is the heat capacity ratio / of the gas and where is the total (stagnation) upstream pressure. For air with a heat capacity ratio =, then =; other gases have in the range 1.09 (e.g. butane) to 1.67 (monatomic gases), so the critical pressure ratio varies in the range < / <, which means that, depending on the gas, choked flow usually ...

  3. Propelling nozzle - Wikipedia

    en.wikipedia.org/wiki/Propelling_nozzle

    Convergent nozzles are used on many jet engines. If the nozzle pressure ratio is above the critical value (about 1.8:1) a convergent nozzle will choke, resulting in some of the expansion to atmospheric pressure taking place downstream of the throat (i.e., smallest flow area), in the jet wake. Although jet momentum still produces much of the ...

  4. Compressor map - Wikipedia

    en.wikipedia.org/wiki/Compressor_map

    A low pressure ratio fan (such as that used on a high bypass ratio turbofan) has a range of working lines. At high flight speeds, the ram pressure ratio factors up the cold nozzle pressure ratio, causing the nozzle to choke. Above the choking condition, the working lines tend to coalesce into a unique steep straight line.

  5. Stodola's cone law - Wikipedia

    en.wikipedia.org/wiki/Stodola's_cone_law

    The pressure ratios for the design flow rate at the intake and outlet are = / and = /, and the off-design ratios are = / and = /. If the speed of sound is reached in a stage, the group of stages can be analyzed until that stage, which is the last in the group, with the remaining stages forming another group of analysis.

  6. Discharge coefficient - Wikipedia

    en.wikipedia.org/wiki/Discharge_coefficient

    In a nozzle or other constriction, the discharge coefficient (also known as coefficient of discharge or efflux coefficient) is the ratio of the actual discharge to the ideal discharge, [1] i.e., the ratio of the mass flow rate at the discharge end of the nozzle to that of an ideal nozzle which expands an identical working fluid from the same initial conditions to the same exit pressures.

  7. Isentropic nozzle flow - Wikipedia

    en.wikipedia.org/wiki/Isentropic_Nozzle_Flow

    As the pressure is reduced still further, a pressure is reached that result in M = 1 at the throat with subsonic flow throughout the remainder of the nozzle. There is another receiver pressure substantially below that of curve C that also results in isentropic flow throughout the nozzle, represented by curve D; after the throat the flow is ...

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  9. Components of jet engines - Wikipedia

    en.wikipedia.org/wiki/Components_of_jet_engines

    The nozzle is usually convergent with a fixed flow area. Supersonic nozzle — For high nozzle pressure ratios (Nozzle Entry Pressure/Ambient Pressure) a convergent-divergent (de Laval) nozzle is used. The expansion to atmospheric pressure and supersonic gas velocity continues downstream of the throat and produces more thrust.