The well-known Fanno-line process deals with a perfect gas flowing in a duct of constant cross-sectional area with friction in which there is no heat transfer to or. Show that the maximum (static) temperature in Rayleigh flow occurs when the a T –s diagram for the system, showing the complete Fanno and Rayleigh lines. It is possible to obtain physical picture of the flow through a normal shock by employing some of the ideas of Fanno line and Rayleigh line Flows. Flow through a.

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Oblique shocks occur when a gas flowing at supersonic speeds strikes a flat or inclined surface. The Rayleigh flow model begins with a differential equation that relates the change in Mach number with the change in stagnation temperatureT 0. The above equation can be manipulated to solve for M as a function of H. Conversely, adding heat to a duct with an upstream, supersonic Mach number will cause the Mach number to decrease until the flow chokes. Equally important to the Fanno flow model is the dimensionless ratio of the change in entropy over the heat capacity at constant pressure, c p.

This page was last edited on 3 Augustat OK Flow of Compressible Fluids.

What are the main assumptions associated with Rayleigh flow? Cooling produces the opposite result for each of those two cases. Each point on the Fanno line will have a different momentum value, and the change in momentum is attributable to the effects of friction.

A stagnation property contains a ‘0’ subscript. On the other hand, for a flow with an upstream Mach number less than 1.


Shock waves and expansion waves Rayleigh flow Fanno flow Assignment

These two models intersect at points on the enthalpy-entropy and Mach number-entropy diagrams, which is meaningful for many applications. Producing a shock wave inside the combustion chamber of an engine due to thermal choking is very undesirable due to the decrease in mass flow rate and thrust.

The Fanno flow model is often used in the design and analysis of nozzles. Flow through a normal shock must satisfy Eqs In other projects Wikimedia Commons.

These values are significant in the design of combustion systems. The characteristic aspect of Rayleigh flow is its involvement of heat transfer.

As was stated earlier, the area and mass flow rate in the duct are held constant for Fanno flow. How do oblique shock wave differ from the normal shock wave? The ratios for the pressure, density, temperature, velocity and stagnation pressure are shown below, respectively. These properties make the Rayleigh flow model applicable for heat addition to the flow through combustion, assuming the heat addition does not result in dissociation of the air-fuel mixture.

Commons category link from Wikidata. The heat addition causes a decrease in stagnation pressurewhich is known as the Rayleigh effect and is critical in the design of combustion systems.

This is also consistent with directional principle indicated by the second law of thermodynamics, i. The average friction factor for the duct is rayleogh to be if the Ma number at the duct exit is 0. To make this website work, we log user data and share it with processors. The Fanno line defines the possible states for a gas when the mass flow rate and total enthalpy are held constant, but the momentum linew.


If initial values of s i and M i are defined, a new equation for dimensionless entropy versus Mach number can be defined for each model.

What do the intersection points of these two curves represent? Fanno flow is the adiabatic flow through a constant lined duct where the effect of friction is considered.

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From Wikipedia, the free encyclopedia. However, the entropy values for each model are not equal at the sonic state. In other projects Wikimedia Commons. Registration Forgot your password? The movement in Figure 4 is always from the left to the right in order to satisfy the second law fanbo thermodynamics.


Additionally, the rqyleigh temperature remains constant. Retrieved from ” https: Air stagnation conditions are Compute. Differential equations can also be developed and solved to describe Rayleigh flow property ratios with respect to the values at the choking location. Download ppt “Shock waves and expansion waves Rayleigh flow Fanno flow Assignment”.

Fanno flow

To use this website, you must agree to our Privacy Policyincluding cookie policy. We think you have liked this presentation. Heat addition will cause both supersonic and subsonic Mach numbers to approach Mach 1, resulting in choked flow.

The differential equation is shown below. The characteristic aspect of Fanno flow is its consideration of friction. This indicates that cooling, instead of heating, causes the Mach number to move from 0.