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Mass injection flow refers to inviscid, adiabatic flow through a constant area duct where the effect of mass addition is considered. For this model, the duct area remains constant, the flow is assumed to be steady and one-dimensional, and mass is added within the duct. Because the flow is adiabatic, unlike in Rayleigh flow, the stagnation temperature is a constant[1]. Compressibility effects often come into consideration, though this flow model also applies to incompressible flow.

For supersonic flow (an upstream Mach number greater than 1), deceleration occurs with mass addition to the duct and the flow can become choked. Conversely, for subsonic flow (an upstream Mach number less than 1), acceleration occurs and the flow can become choked given sufficient mass addition. Therefore, mass addition will cause both supersonic and subsonic Mach numbers to approach Mach 1, resulting in choked flow.


Theory

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The 1D mass injection flow model begins with a mass-velocity relation derived for mass injection into a steady, adiabatic, frictionless, constant area flow of calorically perfect gas:

where represents a mass flux, . This expression describes how velocity will change with a change in mass flux (i.e. how a change in mass flux drives a change in velocity ). From this relation, two distinct modes of behavior are seen:

  1. When flow is subsonic () the quantity is negative, so the right-hand side of the equation becomes positive. This indicates that increasing mass flux will increase subsonic flow velocity toward Mach 1.
  2. When flow is supersonic () the quantity is positive, so the right-hand side of the equation becomes negative. This indicates that increasing mass flux will decrease supersonic flow velocity towards Mach 1.

From the mass-velocity relation, an explicit mass-Mach relation may be derived:

Derivations

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Although Fanno flow and Rayleigh flow are covered in detail in many textbooks, mass injection flow is not.[1][2][3][4] For this reason, derivations of fundamental mass flow properties are given here. In the following derivations, the constant is used to denote the specific gas constant (i.e. ).

Mass-Velocity Relation

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We begin by establishing a relationship between the differential enthalpy, pressure, and density of a calorically perfect gas:

(1)

From the adiabatic energy equation ()[1] we find:

(2)

Substituting the enthalpy-pressure-density relation (1) into the adiabatic energy relation (2) yields

(3)

Next, we find a relationship between differential density, mass flux (), and velocity:

(4)

Substituting the density-mass-velocity relation (4) into the modified energy relation (3) yields

(5)

Substituting the 1D steady flow momentum conservation equation (see also the Euler equations) of the form [5] into (5) yields

(6)

From the ideal gas law we find,

(7)

and from the definition of a calorically perfect gas[1] we find,

(8)

Substituting expressions (7) and (8) into the combined equation (6) yields

(9)

Using the speed of sound in an ideal gas ()[1] and the definition of the Mach number ()[1] yields

(10)
Mass-Velocity Relation

This is the mass-velocity relationship for mass injection into a steady, adiabatic, frictionless, constant area flow of calorically perfect gas.

Mass-Mach Relation

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To find a relationship between differential mass and Mach number, we will find an expression for solely in terms of the Mach number, . We can then substitute this expression into the mass-velocity relation to yield a mass-Mach relation. We begin by relating differential velocity, mach number, and speed of sound:

(11)

We can now re-express in terms of :

(12)

Substituting (12) into (11) yields,

(13)

We can now re-express in terms of :

(14)

By substituting (14) into (13), we can create an expression completely in terms of and . Performing this substitution and solving for yields,

(15)

Finally, expression (15) for in terms of may be substituted directly into the mass-velocity relation (10):

(16)
Mass-Mach Relation

This is the mass-Mach relationship for mass injection into a steady, adiabatic, frictionless, constant area flow of calorically perfect gas.

References

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  1. ^ a b c d e f Anderson, John David (2002). Modern Compressible Flow: With Historical Perspective (3 ed.). New York: McGraw-Hill. ISBN 0072424435.
  2. ^ Shapiro, A.H., The Dynamics and Thermodynamics of Compressible Fluid Flow, Volume 1, Ronald Press, 1953.
  3. ^ Zucker, R.D., Biblarz, O., Fundamentals of Gas Dynamics, John Wiley & Sons, 2002.
  4. ^ Hodge, B.K., and Koenig, K., Compressible Fluid Dynamics with Personal Computer Applications, Prentice Hall, 1995.
  5. ^ "Conservation of Momentum, 1 Dimension, Steady Flow". NASA Glenn Research Center.

Other

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This user has publicly declared that they have a conflict of interest regarding the Wikipedia article David Y. Oh.