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Governing Equation

The energy balance on the control volume reads

$\displaystyle Q = C_p \left({T_0}_2 - {T_0}_1 \right)$

(10.1)

the momentum balance reads

$\displaystyle A ( P_1 - P_2 ) = \dot{m} ( V_2 - V_1)$

(10.2)

The mass conservation reads

$\displaystyle \rho_1 U_1 A = \rho_2 U_2 A = \dot{m}$

(10.3)

Equation of state

$\displaystyle {P_1 \over \rho_1 T_1} = {P_2 \over \rho_2 T_2}$

(10.4)

There are four equations with four unknowns, if the upstream conditions are known (or downstream conditions are known). Thus, a solution can be obtained. One can notice that equations (10.2), (10.3) and (10.4) are similar to the equations that were solved for the shock wave.

$\displaystyle {P_2 \over P_1} = {1 + k{M_1}^{2} \over 1 + k{M_2}^{2}}$

(10.5)

The equation of state (10.4) can further assist in obtaining the temperature ratio as

$\displaystyle {T_2 \over T_1} = {P_2 \over P_1} {\rho_1 \over \rho_2}$

(10.6)

The density ratio can be expressed in terms of mass conservation as

$\displaystyle {\rho_1 \over \rho_2} = {U_2 \over U_1} = { {U_2 \strut \over \sq... ...qrt{kRT_1\strut} } \sqrt{kRT_1\strut} } = {M_2 \over M_1} \sqrt{ T_2 \over T_1}$

(10.7)

Substituting equations (10.5) and (10.7) into equation (10.6) yields

$\displaystyle {T_2 \over T_1} = {1 + k{M_1}^{2} \over 1 + k{M_2}^{2}} {M_2 \over M_1} \sqrt{ T_2 \over T_1}$

(10.8)

Transferring the temperature ratio to the left hand side and squaring the results gives

$\displaystyle {T_2 \over T_1} = \left[ {1 + k{M_1}^{2} \over 1 + k{M_2}^{2}} \right]^{2} \left({M_2 \over M_1}\right)^{2}$

(10.9)

**Figure 10.2:** The temperature entropy diagram for Rayleigh line
$\begin{figure}\centerline{\includegraphics {cont/rayleigh/Ts}} \end{figure}$

The Rayleigh line exhibits two possible maximums one for

and for

. The second maximum can be expressed as $dT/ds = \infty$ . The second law is used to find the expression for the derivative.

$\displaystyle {s_1 -s_2 \over C_p} = \ln {T_2 \over T_1} - {k -1 \over k} \ln {P_2 \over P_1}$

(10.10)

$\displaystyle {s_1 -s_2 \over C_p} = 2 \ln \left[ {({1 + k{M_1}^{2}) \over (1 +... ...ght] + {k -1 \over k} \ln \left[ {1 + k{M21}^{2} \over 1 + k{M_1}^{2} } \right]$

(10.11)

Let the initial condition

, and

be constant and the variable parameters are

, and

. A derivative of equation (10.11) results in

$\displaystyle {1 \over C_p } {ds \over dM} = {2 ( 1 - M^{2} ) \over M (1 + kM^{2} )}$

(10.12)

Taking the derivative of equation (10.12) and letting the variable parameters be

, and

results in

$\displaystyle {dT \over dM} = constant \times { 1 - kM^{2} \over \left( 1 + kM^2\right)^{3} }$

(10.13)

Combining equations (10.12) and (10.13) by eliminating

results in

$\displaystyle {dT \over ds} = constant \times {M (1 - kM^2 ) \over ( 1 -M^2) ( 1 + kM^2 )^2 }$

(10.14)

On T-s diagram a family of curves can be drawn for a given constant. Yet for every curve, several observations can be generalized. The derivative is equal to zero when

or $M = 1 /\sqrt{k}$ or when $M \rightarrow 0$ . The derivative is equal to infinity, $dT/ds = \infty$ when

. From thermodynamics, increase of heating results in increase of entropy. And cooling results in reduction of entropy. Hence, when cooling is applied to a tube the velocity decreases and when heating is applied the velocity increases. At peculiar point of $M = 1 /\sqrt{k}$ when additional heat is applied the temperature decreases. The derivative is negative,

, yet note this point is not the choking point. The choking occurs only when

because it violates the second law. The transition to supersonic flow occurs when the area changes, somewhat similarly to Fanno flow. Yet, choking can be explained by the fact that increase of energy must be accompanied by increase of entropy. But the entropy of supersonic flow is lower (see Figure (10.2)) and therefore it is not possible (the maximum entropy at

.).

It is convenient to refer to the value of . These values are referred to as the ``star''^10.1values. The equation (10.5) can be written between choking point and any point on the curve.

$\displaystyle {P^{*} \over P_1} = {1 + k{M_1}^{2} \over 1 + k}$

(10.15)

The temperature ratio is

$\displaystyle {T^{*} \over T_1} = {1 \over M^2} \left( {1 + k{M_1}^{2} \over 1 + k} \right)^{2}$

(10.16)

$\displaystyle {\rho_1 \over \rho^{*}} = {U^{*} \over U_1} = { {U^{*} \over \sqr... ...U_1 \over \sqrt{kRT_1} } \sqrt{kRT_1} } = {1 \over M_1} \sqrt{ T^{*} \over T_1}$

(10.17)

$\displaystyle {{T_0}_1 \over {T_0}^{*}} = {T_1 \left( 1 + {k -1 \over 2} {M_1}^... ... k ) {M_1}^{2} \over (1 + kM^{2})^2} \left( 1 + {k -1 \over 2} {M_1} ^2 \right)$

(10.18)

The stagnation pressure ratio reads

$\displaystyle {{P_0}_1 \over {P_0}^{*}} = {P_1 \left( 1 + {k -1 \over 2} {M_1}^... ...}\right)} \left( { 1 + k{M_1}^2 \over {(1 + k) \over 2}} \right)^{k \over k -1}$

(10.19)

Next: Rayleigh Flow Tables Up: Rayleigh Flow Previous: Introduction Index

Created by:Genick Bar-Meir, Ph.D.
On: 2007-11-21