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))