Compressible Flow credits Logo credits
Potto Home Contact Us

Potto Home

About Potto


  Hard copy
  Gas Dynamics Tables

Other things:
Other resources
Download Area

Other Resources

  Compare Other Books

Potto Statistics



next up previous index
Next: Mass Flow Rate (Number) Up: Isentropic Converging-Diverging Flow in Previous: Relationship Between the Mach   Index

Isentropic Flow Examples

Air is allowed to flow from a reservoir with temperature
of $21^{\...
Assume that the ratio of specific heat is $ k=C_p / C_v = 1.4$.


The stagnation conditions at the reservoir will be maintained through out tube because the process is isentropic. Hence the stagnation temperature can be written $ T_{0} = constant$ and $ P_{0} = constant$ and both of them are known (the condition at the reservoir). For the point where the static pressure is known, the Mach number can be calculated utilizing the pressure ratio. With known Mach number, the temperature, and velocity can be calculated. Finally, the cross section can be calculated with all these information.

In the point where the static pressure is known

$\displaystyle \bar{P} = {P \over P_0} = {3 [MPa] \over 5 [MPa] } = 0.6

From Table (4.2) or from Figure (4.3) or by utilizing the enclosed program, Potto-GDC, or simply by using the equations that
Isentropic Flow Input: Pbar k = 1.4
M T/T0 ρ/ρ0 A/A* P/P0 PAR F/F*
0.886393 0.864201 0.694283 1.01155 0.6 0.606928 0.531054

With these values the static temperature and the density can be calculated.

$\displaystyle T$ $\displaystyle = 0.86420338 \times (273+ 21) = 254.076 K$    
$\displaystyle \rho$ $\displaystyle = {\rho \over \rho_0} \overbrace{P_{0}\over R T_0}^{\rho_0}= 0.69... {5 \times 10^6 [Pa] \over 287.0 \left[{J \over kg K}\right] \times 294 [K] }$    
  $\displaystyle = 41.1416 \left[{kg \over m^3 }\right]$    

The velocity at that point is

$\displaystyle U = M \overbrace{\sqrt{kRT}}^{c} = 0.88638317 \times
\sqrt { 1.4 \times 287 \times 294} = 304 [m /sec]

The tube area can be obtained from the mass conservation as

$\displaystyle A = {\dot {m} \over \rho U} = 8.26 \times 10^{-5} [m^{3}]

For a circular tube the diameter is about 1[cm].

The Mach number at point A on tube is measured to be
...hat the specific heat ratio $k=1.4$ and assume a perfect
gas model.
\end{examl} 4.3 4.4


With known Mach number at point A all the ratios of the static properties to total (stagnation) properties can be calculated. Therefore, the stagnation pressure at point A is known and stagnation temperature can be calculated.

At $ M=2$ (supersonic flow) the ratios are

Isentropic Flow Input: M k = 1.4
M T/T0 ρ/ρ0 A/A* P/P0 PAR F/F*
2 0.555556 0.230048 1.6875 0.127805 0.21567 0.593093

With this information the pressure at Point B expressed

% latex2html id marker 50331
$\displaystyle {P_{A} \over P_{0}} = \overbrace{P_...
...2}} \times {P_{A} \over P_{B}} = 0.12780453 \times {2.0 \over 1.5} = 0.17040604$    

The corresponding Mach number for this pressure ratio is 1.8137788 and $ T_{B} = 0.60315132$ $ {P_{B} \over P_{0} }= 0.17040879$ . The stagnation temperature can be ``bypassed'' to calculated the temperature at point $ \mathbf{B}$
$\displaystyle T_{B} = T_{A}\times \overbrace{T_{0} \over T_{A} }^{M=2} \times \...
.....} = 250 [K] \times {1 \over 0.55555556} \times {0.60315132} \simeq 271.42 [K]$    

Gas flows through a converging-diverging duct.
At point \lq\lq A'' the...
...that the flow is isentropic and the gas specific heat ratio
is 1.4.


To obtain the Mach number at point B by finding the ratio of the area to the critical area. This relationship can be obtained by
$\displaystyle {A_{B} \over A{*} } = {A _{B} \over A_{A} } \times {A_{A} \over A...
...4 }^{\hbox{from the Table \eqref{variableArea:tab:basicIsentropic}}} = 1.272112$    

With the value of $ {A_{B} \over A{*} } $ from the Table (4.2) or from Potto-GDC two solutions can be obtained. The two possible solutions: the first supersonic M = 1.6265306 and second subsonic M = 0.53884934. Both solution are possible and acceptable. The supersonic branch solution is possible only if there where a transition at throat where M=1.
Isentropic Flow Input: A/A* k = 1.4
M T/T0 ρ/ρ0 A/A* P/P0 PAR F/F*
0.538865 0.945112 0.868378 1.27211 0.820715 1.04404 0.611863
1.62655 0.653965 0.345848 1.27211 0.226172 0.287717 0.563918

next up previous index
Next: Mass Flow Rate (Number) Up: Isentropic Converging-Diverging Flow in Previous: Relationship Between the Mach   Index
Created by:Genick Bar-Meir, Ph.D.
On: 2007-11-21