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The ratio of the area of the narrowest part of the nozzle to the exit plane area is mainly what determines how efficiently the expansion of the exhaust gases is converted into linear velocity, the exhaust velocity, and therefore the thrust of the rocket engine. The gas properties have an effect as well.
As of 2009, the search for various schemes to achieve higher area ratios for rocket nozzles remains an active field of research and patenting. [ 1 ] [ 2 ] Generally, modern application of these designs can be divided into "air-to-vacuum" engines, which start their work at sea level and finish it at vacuum conditions, and "vacuum" engines, which ...
Because of the atmospheric boundary, the atmospheric pressure affects the exit area ratio so that atmospheric compensation can be obtained up to the geometric maximum allowed by the specific nozzle. The nozzle operates in two distinct modes: open and closed. In closed wake mode, the exhaust gas fills the entire nozzle exit area.
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.
Multiple large spiral nozzles (also known as pigtail nozzles) used in a scrubber application. Spiral nozzles typically have the largest free passage design to help prevent clogging. Rocket motors maximise thrust and exhaust velocity by using convergent-divergent nozzles with very large area ratios and therefore extremely high pressure ratios ...
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 by mass flow rate. Used to check experimental rocket's combustion ...
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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.