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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OK Flow of Compressible Fluids. For this model, the duct area remains constant and no mass is added within the duct. Point 3 labels the end of the nozzle where the fznno transitions from isentropic to Fanno. Rayleigh flow refers to frictionless, non- Adiabatic flow through a constant area duct where the effect of heat addition or rejection is considered. 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.

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. Calculate the stagnation pressure and Mach number upstream of the shock, as well as pressure, temperature, velocity, Mach number and stagnation pressure rayldigh the shock.

What are the main assumptions associated with Fanno flow? On the other hand, for a flow with an upstream Mach number less than 1. Oblique shocks occur when a gas flowing at supersonic speeds strikes a flat or inclined surface. Conversely, heat rejection decreases a subsonic Mach number and increases a supersonic Mach number along the duct.


My presentations Profile Feedback Log out. The above equation can be rewritten in terms of a static to stagnation temperature ratio, which, for a calorically perfect gas, is equal to the dimensionless enthalpy ratio, H:.

Air stagnation conditions are Compute. The differential equation is shown below. Each point on the Fanno line corresponds with a different Mach number, and the movement to choked flow is shown in the diagram.

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Shock waves and expansion waves Rayleigh flow Fanno flow Assignment

Conversely, the Mach number of a supersonic flow will decrease until the flow is choked. Fanno flow is named after Gino Girolamo Fanno. Compressibility effects often come into consideration, although the Rayleigh flow model certainly also applies to incompressible flow.

The Rayleigh flow model is also used extensively with the Fanno flow model.

What do the intersection points of these two curves represent? This page was last edited on 23 Julyat Registration Forgot your password? The Fanno flow model is often used in the design and analysis of nozzles. The Fanno flow model is considered an irreversible process due to viscous effects.


Cooling produces the opposite result for each of those two cases. By using this site, you agree to the Terms of Use and Privacy Policy. Producing a liens 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.

For instance, the combustion chambers inside turbojet engines usually have a constant area and the fuel mass addition is negligible. Retrieved from ” https: Conversely, adding heat to a duct with an upstream, supersonic Mach number will cause the Mach number to decrease until the flow chokes.


How do oblique shock wave differ from the normal shock wave? However, the entropy values for each model are not equal at the sonic state. However, these figures show the shock wave before it has moved entirely through the duct. Linfs intersection points are calculated by equating the new dimensionless entropy equations with each other, resulting in the relation below. These two models intersect at points on the enthalpy-entropy and Mach number-entropy diagrams, which is meaningful for many applications.

For given upstream conditions at point 1 as shown in Figures 3 and 4, calculations can be made to determine the nozzle exit Mach number and the location of a normal shock in the constant area duct. 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.

Fanno flow – Wikipedia

However, the entropy values for raylsigh model are not equal at the sonic state. The Fanno line represents the states that satisfy the conservation of mass and energy equations. The Rayleigh line does not satisfy Eq. First Law limes Thermodynamics-The Energy Equation 4 Work transfer can also occur at the control surface when a force associated with fluid normal stress. They are represented graphically along with the stagnation temperature ratio equation from the previous section.