| Recap |
| In
this course you have learnt the following |
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- Fluid density varies mainly due
to a large Ma flow. This leads to a situation where
continuity & momentum equation can be coupled to the energy
equation and the equation of state to solve four unknowns-
P, T, V, ρ.
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- The stagnation enthalpy
and hence T0 are conserved in isentropic flows. The effect
of area variation in on flow properties in an isentropic
flow is of great significance. This reveals the phenomenon
of choking at the sonic velocity in the throat of a nozzle.
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- At choke condition, the ratio of
throat pressure to stagnation pressure is constant and is
equal to 0.528 for γ =1.4.
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- At supersonic
velocities, the normal shock wave appears across which the
gas discontinuity reverts to the subsonic conditions.
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- Fanno and Rayleigh line
flows both entail choking of the exit flow. The conditions
before and after a normal shock are defined by the points of
intersection of Fanno and Rayleigh lines on a T-s Diagram.
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- If a supersonic flow is
made to change its direction, the oblique shock is evolved.
The oblique shock continues to bend in the downstream
direction until the Mach Number of the velocity component
normal to the wave is unity.
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Congratulations! you have finished Chapter
12. |
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