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  2. Propelling nozzle - Wikipedia

    en.wikipedia.org/wiki/Propelling_nozzle

    The convergent nozzle was replaced with a C-D nozzle on the same engine J57 in the same aircraft F-101. The increased thrust from the C-D nozzle (2,000 lb, 910 kg at sea-level take-off) on this engine raised the speed from Mach 1.6 to almost 2.0 enabling the Air Force to set a world's speed record of 1,207.6 mph (1,943.4 km/h) which was just ...

  3. de Laval nozzle - Wikipedia

    en.wikipedia.org/wiki/De_Laval_nozzle

    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. It is used to accelerate a compressible fluid to supersonic speeds in the axial (thrust) direction, by converting the thermal energy of the flow into kinetic energy .

  4. Components of jet engines - Wikipedia

    en.wikipedia.org/wiki/Components_of_jet_engines

    Exhaust or nozzle — Turbine exhaust gases pass through the propelling nozzle to produce a high velocity jet. 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 ...

  5. Isentropic nozzle flow - Wikipedia

    en.wikipedia.org/wiki/Isentropic_Nozzle_Flow

    A nozzle for a supersonic flow must increase in area in the flow direction, and a diffuser must decrease in area, opposite to a nozzle and diffuser for a subsonic flow. So, for a supersonic flow to develop from a reservoir where the velocity is zero, the subsonic flow must first accelerate through a converging area to a throat, followed by ...

  6. Nozzle - Wikipedia

    en.wikipedia.org/wiki/Nozzle

    A de Laval nozzle has a convergent section followed by a divergent section and is often called a convergent-divergent (CD) nozzle ("con-di nozzle"). Convergent nozzles accelerate subsonic fluids. If the nozzle pressure ratio is high enough, then the flow will reach sonic velocity at the narrowest point (i.e. the nozzle throat). In this ...

  7. Rocket engine nozzle - Wikipedia

    en.wikipedia.org/wiki/Rocket_engine_nozzle

    The nozzle's throat should have a smooth radius. The internal angle that narrows to the throat also has an effect on the overall efficiency, but this is small. The exit angle of the nozzle needs to be as small as possible (about 12°) in order to minimize the chances of separation problems at low exit pressures.

  8. Pratt & Whitney F119 - Wikipedia

    en.wikipedia.org/wiki/Pratt_&_Whitney_F119

    The rectangular convergent-divergent nozzle is fully variable for both the convergent throat and divergent areas for high nozzle pressure ratio and can vector ±20° in the pitch axis, greatly improving the aircraft's pitch authority by augmenting the pitching moment of the tail with engine thrust; this enables the F-22 to remain controllable ...

  9. Engine pressure ratio - Wikipedia

    en.wikipedia.org/wiki/Engine_pressure_ratio

    The engine pressure ratio (EPR) is the total pressure ratio across a jet engine, measured as the ratio of the total pressure at the exit of the propelling nozzle divided by the total pressure at the entry to the compressor. [1] Jet engines use either EPR or compressor/fan RPM as an indicator of thrust. [2]