def test_sigma_def_massflow(m):
assert mf.Sigma_Mach(m, gamma=1.3) == pytest.approx(
mf.WeightMassFlow(1., gamma=1.3) / mf.WeightMassFlow(m, gamma=1.3))
import aerokit.aero.MassFlow as mf
plt.rcParams['font.size'] = 14
plt.rcParams['lines.linewidth'] = 1.5
# for slides
#plt.rcParams['font.size'] = 24 ; plt.rcParams['grid.linewidth'] = 2 ; plt.rcParams['lines.linewidth'] = 4
npoints = 100
gam = 1.4
Mmin = 0.1
Mmax = 4.
Mach = np.log10(np.logspace(Mmin, Mmax, npoints + 1))
debr = mf.WeightMassFlow(Mach, gam)
sig = mf.Sigma_Mach(Mach, gam)
fig = plt.figure(1, figsize=(10, 8))
#fig.suptitle('Ratio to critical state, $\gamma = %.1f$'%gam, y=0.93)
plt.plot(Mach, debr, 'k-')
#plt.axis([Mmin, Mmax, 0., 4.])
plt.xlabel('Mach number')
plt.ylabel('weighted mass flow')
#plt.minorticks_on()
plt.grid(which='major', linestyle=':', alpha=0.8)
#plt.grid(which='minor', linestyle=':', alpha=0.5)
fig.savefig('fct-weightedmf.pdf', bbox_inches='tight')
plt.show()
fig = plt.figure(2, figsize=(10, 8))
