This includes convergent and convergent-divergent nozzles that may be fixed or geometrically variable.

Rocket motors also employ convergent-divergent nozzles, but these are usually of fixed geometry, to minimize weight.

Plug nozzles have been shown to provide noise reduction compared to traditional convergent-divergent nozzles.

For a supersonic flight Mach number, acceleration is typically achieved via a convergent-divergent nozzle.

If an acceleration to supersonic flow is required, a convergent-divergent nozzle is required.

However, these nozzles had much lower aeropropulsive performance than the convergent-divergent nozzle at Mach numbers greater than 0.60.

Thrust is provided by the combustion products exiting the engine at high velocity, via a fixed area ratio convergent-divergent nozzle.

The low pressure draws the suction fluid into the convergent-divergent nozzle where it mixes with the motive fluid.

A large evacuated dump tank is separated from the downstream end of a convergent-divergent nozzle by a diaphragm or fast acting valve.

Convergent-divergent nozzles can therefore accelerate fluids that have choked in the convergent section to supersonic speeds.

Fluid under high pressure is converted into a high-velocity jet at the throat of the convergent-divergent nozzle which creates a low pressure at that point.

VASIMR can be most basically thought of as a convergent-divergent nozzle for ions and electrons.

The gas passes through a convergent-divergent nozzle before entering the mixing chamber, and then exits through a convergent nozzle.

Rocket motors maximise thrust and exhaust velocity by using convergent-divergent nozzles with very large area ratios and therefore extremely high pressure ratios.

The cruciform-shaped convergent-divergent nozzle turned the flow for thrust vectoring by deflecting the divergent surfaces of the nozzle, called flaps.

A de Laval nozzle has a convergent section followed by a divergent section and is often called a convergent-divergent nozzle ("con-di nozzle").

Combustion in a ramjet takes place at subsonic velocities, similar to turbojets, but the combustion products are then accelerated through a convergent-divergent nozzle to supersonic speeds.

The "F" indicated it was fitted with the VK-1F engine with an afterburner by modifying the rear fuselage with a new convergent-divergent nozzle and fuel system.

The second phase is a strong electromagnet positioned to compress the ionized plasma in a similar fashion to a convergent-divergent nozzle that compresses gas in traditional rocket engines.

In essence, the pressure energy of the inlet motive fluid is converted to kinetic energy in the form of velocity head at the throat of the convergent-divergent nozzle.

As this unsteady expansion propagates through the long tube, it sets up a steady subsonic flow toward the nozzle, which is accelerated by the convergent-divergent nozzle to a supersonic condition.

BFC based models of transition duct and convergent-divergent nozzle flows have been created in order to provide nozzle exit plane conditions for round, rectangular and elliptic nozzle shapes.

Convergent-divergent nozzles can give supersonic jet velocity within the divergent section, whereas in a convergent nozzle the exhaust fluid cannot exceed the speed of sound of the gas within the nozzle.

A de Laval nozzle (or convergent-divergent nozzle, CD nozzle or con-di nozzle) is a tube that is pinched in the middle, making a carefully balanced, asymmetric hourglass shape.

The obvious result is that in order to accelerate a flow to supersonic, one needs a convergent-divergent nozzle, where the converging section accelerates the flow to sonic speeds, and the diverging section continues the acceleration.

This includes convergent and convergent-divergent nozzles that may be fixed or geometrically variable.

Rocket motors also employ convergent-divergent nozzles, but these are usually of fixed geometry, to minimize weight.

Plug nozzles have been shown to provide noise reduction compared to traditional convergent-divergent nozzles.

For a supersonic flight Mach number, acceleration is typically achieved via a convergent-divergent nozzle.

If an acceleration to supersonic flow is required, a convergent-divergent nozzle is required.

However, these nozzles had much lower aeropropulsive performance than the convergent-divergent nozzle at Mach numbers greater than 0.60.

Thrust is provided by the combustion products exiting the engine at high velocity, via a fixed area ratio convergent-divergent nozzle.

The low pressure draws the suction fluid into the convergent-divergent nozzle where it mixes with the motive fluid.

A large evacuated dump tank is separated from the downstream end of a convergent-divergent nozzle by a diaphragm or fast acting valve.

Convergent-divergent nozzles can therefore accelerate fluids that have choked in the convergent section to supersonic speeds.

Fluid under high pressure is converted into a high-velocity jet at the throat of the convergent-divergent nozzle which creates a low pressure at that point.

VASIMR can be most basically thought of as a convergent-divergent nozzle for ions and electrons.

The gas passes through a convergent-divergent nozzle before entering the mixing chamber, and then exits through a convergent nozzle.

Rocket motors maximise thrust and exhaust velocity by using convergent-divergent nozzles with very large area ratios and therefore extremely high pressure ratios.

The cruciform-shaped convergent-divergent nozzle turned the flow for thrust vectoring by deflecting the divergent surfaces of the nozzle, called flaps.

A de Laval nozzle has a convergent section followed by a divergent section and is often called a convergent-divergent nozzle ("con-di nozzle").

Combustion in a ramjet takes place at subsonic velocities, similar to turbojets, but the combustion products are then accelerated through a convergent-divergent nozzle to supersonic speeds.

The "F" indicated it was fitted with the VK-1F engine with an afterburner by modifying the rear fuselage with a new convergent-divergent nozzle and fuel system.

The second phase is a strong electromagnet positioned to compress the ionized plasma in a similar fashion to a convergent-divergent nozzle that compresses gas in traditional rocket engines.

In essence, the pressure energy of the inlet motive fluid is converted to kinetic energy in the form of velocity head at the throat of the convergent-divergent nozzle.

As this unsteady expansion propagates through the long tube, it sets up a steady subsonic flow toward the nozzle, which is accelerated by the convergent-divergent nozzle to a supersonic condition.

BFC based models of transition duct and convergent-divergent nozzle flows have been created in order to provide nozzle exit plane conditions for round, rectangular and elliptic nozzle shapes.

Convergent-divergent nozzles can give supersonic jet velocity within the divergent section, whereas in a convergent nozzle the exhaust fluid cannot exceed the speed of sound of the gas within the nozzle.

A de Laval nozzle (or convergent-divergent nozzle, CD nozzle or con-di nozzle) is a tube that is pinched in the middle, making a carefully balanced, asymmetric hourglass shape.

The obvious result is that in order to accelerate a flow to supersonic, one needs a convergent-divergent nozzle, where the converging section accelerates the flow to sonic speeds, and the diverging section continues the acceleration.