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roldy
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I'm working on an interaction project for my propulsion class. I am to do an analysis on a quasi-one-dimensional air flow in a duct that is 1 meter long.
Length 1 meter
Isentropic flow
no work interaction
[tex]P_0=101325[/tex]Pa
[tex]T_0=288[/tex]K
Mach=0.5
cross-section area at inlet=0.1 m^2
cross-section area at exit=0.4345 m^2
I'm to perform 100,000 iterations from the inlet to the exit to calculate the exit conditions
P, T, velocity, Mach, P total, T total.
We are to use differential analysis. I wrote MATLAB code to perform this analysis but I'm also required to check my results against analytical results.
Could someone explain to me how to calculate the analytical results?
The exit conditions as calculated from my program are as follow below. Attached is my code.Exit pressure = 101325.9571 Pa
Exit temperature = 288.0015 K
Exit velocity = 168.8889 m/s
Exit Mach = 0.49997
Exit total pressure = 191802.8588 Pa
Exit total temperature = 86.3911 K
Exit density = 0.28613 kg/m^3
P/P*= 0.99999
rho/rho*= 4.3448
T/T*= 0.99999
U/U*= 1.0001
Pt/Pt*= 0.62665
Tt/Tt*= 3.5004
Length 1 meter
Isentropic flow
no work interaction
[tex]P_0=101325[/tex]Pa
[tex]T_0=288[/tex]K
Mach=0.5
cross-section area at inlet=0.1 m^2
cross-section area at exit=0.4345 m^2
I'm to perform 100,000 iterations from the inlet to the exit to calculate the exit conditions
P, T, velocity, Mach, P total, T total.
We are to use differential analysis. I wrote MATLAB code to perform this analysis but I'm also required to check my results against analytical results.
Could someone explain to me how to calculate the analytical results?
The exit conditions as calculated from my program are as follow below. Attached is my code.Exit pressure = 101325.9571 Pa
Exit temperature = 288.0015 K
Exit velocity = 168.8889 m/s
Exit Mach = 0.49997
Exit total pressure = 191802.8588 Pa
Exit total temperature = 86.3911 K
Exit density = 0.28613 kg/m^3
P/P*= 0.99999
rho/rho*= 4.3448
T/T*= 0.99999
U/U*= 1.0001
Pt/Pt*= 0.62665
Tt/Tt*= 3.5004
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