Civil Engineering (CE) : Recap - Compressible Flow Civil Engineering (CE) Notes | EduRev
In this course you have learnt the following
- 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.
- 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.
- At choke condition, the ratio of throat pressure to stagnation pressure is constant and is equal to 0.528 for γ=1.4.
- At supersonic velocities, the normal shock wave appears across which the gas discontinuity reverts to the subsonic conditions.
- 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.
- 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.