aero.Isentropic

In [1]:

import aerokit.aero.Isentropic as Is

import aerokit.aero.Isentropic as Is

What are the pressure and temperature at the stagnation point in front of a subsonic upstream flow with $M_0=0.8$, and respective $10^5$ Pa and $280$ K?

In [2]:

M0=0.8
Pstag = 1.e5 * Is.PtPs_Mach(M0)
Tstag = 280. * Is.TtTs_Mach(M0)
print("Stagnation pressure and temperature are {:.4e} Pa and {:.2f} K".format(Pstag, Tstag))

M0=0.8 Pstag = 1.e5 * Is.PtPs_Mach(M0) Tstag = 280. * Is.TtTs_Mach(M0) print("Stagnation pressure and temperature are {:.4e} Pa and {:.2f} K".format(Pstag, Tstag))

Stagnation pressure and temperature are 1.5243e+05 Pa and 315.84 K

Consider a nozzle in which a perfect gas with specific constant $\gamma = 1.1$ flows isentropically. The total pressure of the flow and the pressure at the end of the flow are respectively $ P_t = 0.45$ atm and $P = 10$ atm. Find the exit Mach of this flow.

In [3]:

atm = 1.01*10.e5

P = 10*atm
Pt = 0.45*atm

M = Is.Mach_PtPs(P/Pt, 1.1)
print("The exit Mach number of this flow is M = {:.2f}".format(M))

atm = 1.01*10.e5 P = 10*atm Pt = 0.45*atm M = Is.Mach_PtPs(P/Pt, 1.1) print("The exit Mach number of this flow is M = {:.2f}".format(M))

The exit Mach number of this flow is M = 2.55

Consider air in a pipe. The air has a temperature of $T = 390$ K and a total temperature of $T_t = 280$ K. What is the Mach number of the air flowing through the pipe?

In [4]:

Tt = 280
T = 390
M = Is.Mach_TtTs(T/Tt)
print("The Mach number of this flow is M = {:.2f}".format(M))

Tt = 280 T = 390 M = Is.Mach_TtTs(T/Tt) print("The Mach number of this flow is M = {:.2f}".format(M))

The Mach number of this flow is M = 1.40

What is the velocity of the air flowing through the pipe?

In [5]:

V = Is.Velocity_MachTt(M, Tt)
print("The velocity of the air flowing though the pipe is V = {:.2f} m/s".format(V))

V = Is.Velocity_MachTt(M, Tt) print("The velocity of the air flowing though the pipe is V = {:.2f} m/s".format(V))

The velocity of the air flowing though the pipe is V = 398.39 m/s