475
Appendix A: COMPROP2 Code for
Compressible Flow Properties
Introduction
COMPROP2 is an interactive Window-based software program for the calculation of com-
pressible ow properties. This program was developed by Dr. A. J. Ghajar, regents profes-
sor of mechanical and aerospace engineering at Oklahoma State University, Dr. L. M. Tam,
professor of electromechanical engineering at University of Macau, and C. W. Pau, former
research associate of electromechanical engineering at University of Macau.
The program consists of six modules, isentropic ow, normal shock wave, oblique shock
wave, Fanno ow (adiabatic and isothermal ow with friction), and Rayleigh ow (ow
with heat transfer), and airfoil (supersonic airfoil analysis). By default, a specic heat ratio
of 1.4 (the value for air at standard conditions) is assumed. However, the value of the spe-
cic heat ratio can be changed in all modules in the specic heat ratio (gamma) EditBox.
The use of each of the modules will now be briey discussed. The COMPROP2 program
and a detailed User’s Manual providing a more detailed explanation of each of the six
modules and 17 worked out example problems are available through the book website at
www.crcpress.com.
Isentropic Flow Module
Click the icon on the left panel and the Isentropic Flow window will pop up. This module
allows the user to input one of the following six parameters:
1. Mach number (M)
2. Stagnation-to-static pressure ratio (p
0
/p)
3. Stagnation-to-static temperature ratio (T
0
/T)
4. Stagnation-to-static density ratio (ρ
0
/ρ)
5. Area ratio (A/A*)
6. Prandtl–Meyer angle
To enter a value, click on the corresponding EditBox, enter the value, and press ENTER.
The corresponding values of the other ve parameters are then displayed. All results will
also print on the datasheet at the right, and a log le for later analysis or printout is generated.
Instead of inputting the value in the EditBox, the user can alternatively pick the input
data from a graph. The procedure in this case is as follows:
476 Appendix A
Click the button, a graph will pop up. The graph properties are as follows:
X-axis: Mach number
Y-axis: numerical value of required property
Aqua line: stagnation-to-static pressure ratio (p
0
/p)
Blue line: stagnation-to-static density ratio (ρ
0
/ρ)
Red line: stagnation-to-static temperature ratio (T
0
/T)
Green line: area ratio (A/A*)
Move the mouse cursor over the graph; slide the black line to the desired Mach number.
As the line is sliding, corresponding properties for that Mach number are interactively
displayed on right panel. When the desired Mach number or property is selected, the user
can click the mouse and the result will be recorded in the datasheet and in the log le.
Normal Shock Wave Module
Click the icon on the left panel and the Normal Shock Wave window will pop up. This
module allows the user to input one of the following six parameters:
1. Mach number ahead of the shock wave (M
1
)
2. Mach number behind the shock wave (M
2
)
3. Stagnation pressure ratio across the shock wave (p
02
/p
01
)
4. Static pressure ratio across the shock wave (p
2
/p
1
)
5. Static temperature ratio across the shock wave (T
2
/T
1
)
6. Stagnation-to-static pressure ratio across the shock wave (p
02
/p
1
)
To enter a value, click on the corresponding EditBox, enter the value, and press ENTER.
The corresponding values of the other ve parameters and of the static density ratio across
the shock wave (ρ
2
/ρ
1
) are then displayed. All results will also print on the datasheet at the
right, and a log le for later analysis or printout is generated.
Instead of inputting the value in the EditBox, the user can again alternatively pick the
input data from a graph. The procedure in this case is as follows:
Click the button, a graph will pop up. The graph properties are as follows:
X-axis: Mach number ahead of the shock wave
Y-axis: log scale of numerical value
Aqua line: static pressure ratio across the shock wave (p
2
/p
1
)
Blue line: static density ratio across the shock wave (ρ
2
/ρ
1
)
Red line: static temperature ratio across the shock wave (T
2
/T
1
)
Fuchsia line: stagnation pressure ratio across the shock wave (p
02
/p
01
)
Green line: stagnation-to-static pressure ratio across the shock wave (p
02
/p
1
)
Lime line: Mach number behind the shock wave (M
2
)

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