Abstract
In this experiment we studies the
pressure distribution over a convergent divergent nozzle for subsonic and
supersonic flow, the nozzle was inside a reservoir, we calculated the pressure
ratios and put them in the isentropic relations to obtain the Mach number .
Introduction
A nozzle is a
relatively simple device, just a specially shaped tube through which hot gases
flow. Ramjets and rockets typically use a fixed convergent section followed by
a fixed divergent section for the design of the nozzle. This nozzle
configuration is called a convergent-divergent, or CD,
nozzle. In a CD nozzle, the hot exhaust leaves the combustion chamber and
converges down to the minimum area, or throat, of the nozzle.
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