No, bullets are accelerated by rapidly expanding gasses. Those gasses are in a cylinder only open at one end. The bullet acts as a piston, and is pushed out of the open end of the cylinder. Not all bullets are supersonic, but those that are become supersonic from the amount of acceleration, and the time it is applied.
Supersonic flow is produced in a de laval nozzle by constricting the flow in the center in order to increase the velocity. The shape will be hour-glass in nature. The initial mass flow rate and inlet pressure must be sufficient to produce a supersonic choked flow and the discharge pressure must be sufficiently low enough for supersonic flow to occur.
One disadvantage in the convergent-divergent nozzle as a shock wave can take place in the nozzle A nozzle is a device that converts pressure energy to kinetic energy (increasing fluid velocity on the account of static pressure) For a convergent nozzle there is no disadvantages as it can raise the fluid velocity only for the sonic speed the convergent-divergent type raises the velocity to over than sonic speed making supersonic flow, this could make a shock wave in the nozzle that turns the supersonic flow to subsonic flow
If the flow is subsonic the pressure will increase, if however it is supersonic the pressure will decrease.
A Hartmann generator is an electronic device that produces shock waves. It does this on the edge of a nozzle using a supersonic gas resonate.
too bad i dont know what either of those are
High Pressure Turbine
Using shock-expansion cancellation technique flow in the diverging part of a supersonic nozzle is brought back to free stream direction ( direction parallel to the axis of nozzle) where a rhombus shaped region(Test Section) is formed in which uniform flow is ensured. Refer Method Of Characteristics from Rathakrishnan For Diagram.
In the converging section of the nozzle,relatively high pressure expanding has a small increase in specific volume. At lower pressures the increase in specific volume is large.
Laurence D. Leavitt has written: 'Effects of spanwise nozzle geometry and location on the longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds' -- subject(s): Aerodynamics, Supersonic, Supersonic Aerodynamics, Supersonic nozzles 'Effects of twin-vertical-tail parameters on twin-engine afterbody/nozzle aerodynamic characteristics' -- subject(s): Fighter planes, Jet nozzles, Tail surfaces, Flight testing 'Static internal performance characteristics of two thrust-reverser concepts for axisymmetric nozzles' -- subject(s): Jet planes, Thrust reversers, Mathematical models, Testing 'Longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds' -- subject(s): Aerodynamics, Supersonic, Supersonic Aerodynamics, Supersonic nozzles 'Effect on empennage location on twin-engine afterbody/nozzle aerodynamic characteristics at Mach numbers from 0.6 to 1.2' -- subject(s): Flight testing, Air-engines, Fighter planes
Allen E. Puckett has written: 'Guided missile engineering' -- subject(s): Guided missiles 'Supersonic nozzle design for engineers'
G. T. Golesworthy has written: 'The performance of a conical convergent-divergent nozzle with area ratio 2.9 in external flow' -- subject(s): Supersonic nozzles
George G Mateer has written: 'Charts for equilibrium and frozen nozzle flows of carbon dioxide' -- subject(s): Carbon dioxide, Gas dynamics, Supersonic nozzles