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 situation, the nozzle is said to be choked. Increasing the nozzle pressure ratio further will not increase the throat Mach number above one. Downstream (i.e. external to the nozzle) the flow is free to expand to supersonic velocities; however, Mach 1 can be a very high speed for a hot gas because the speed of sound varies as the square root of absolute temperature. This fact is used extensively in rocketry where hypersonic flows are required and where propellant mixtures are deliberately chosen to further increase the sonic speed. Divergent nozzles slow fluids if the flow is subsonic, but they accelerate sonic or supersonic fluids. Convergent-divergent nozzles can therefore accelerate fluids that have choked in the convergent section to supersonic speeds. This CD process is more efficient than allowing a convergent nozzle to expand supersonically externally. The shape of the divergent section also ensures that the direction of the escaping gases is directly backwards, as any sideways component would not contribute to thrust. Propelling A jet exhaust produces thrust from the energy obtained from burning fuel. The hot gas is at a higher pressure than the outside air and escapes from the engine through a propelling nozzle, which increases the speed of the gas. Exhaust speed needs to be faster than the aircraft speed in order to produce thrust but an excessive speed difference wastes fuel (poor propulsive efficiency). Jet engines for subsonic flight use convergent nozzles with a sonic exit velocity. Engines for supersonic flight, such as used for fighters and SST aircraft (e.g. Concorde) achieve the high exhaust speeds necessary for supersonic flight by using a divergent extension to the convergent engine nozzle which accelerates the exhaust to supersonic speeds. Rocket motors maximise thrust and exhaust velocity by using convergent-divergent nozzles with very large area ratios and therefore extremely high pressure ratios. Mass flow is at a premium because all the propulsive mass is carried with vehicle, and very high exhaust speeds are desirable. Magnetic Magnetic nozzles have also been proposed for some types of propulsion, such as VASIMR, in which the flow of plasma is directed by magnetic fields instead of walls made of solid matter. Spray Many nozzles produce a