FSpi3 = np.ones(npts+1) FSm3 = M3sup*np.ones(npts+1) plt.subplot(311) plt.plot(FSalpha, FSpi3, '-', color='#ff0000') plt.subplot(312) plt.plot(FSalpha, FSpi4, '-', color='#ff0000') plt.subplot(313) plt.plot(FSalpha, FSm3, '-', color='#ff0000') # --- (CW) conventional working state # M8 is sonic so M4 is known CWm4 = mf.Mach_Sigma(A3A2/A8A2, .1, gam) # look for subsonic value CWm3low = sw.downstream_Mn(M3sup, gam) alphamin = ray.Ti_Ticri(CWm4, gam)/ray.Ti_Ticri(CWm3low, gam) CWm3high = mf.Mach_Sigma(A3A2*mf.Sigma_Mach(sw.downstream_Mn(M2, gam), gam), .1, gam) alphamax = ray.Ti_Ticri(CWm4, gam)/ray.Ti_Ticri(CWm3high, gam) print " unstart of inlet throat for Ti4/Ti0 = %6.3f"%(alphamax) print " fully supersonic flow for Ti4/Ti0 = %6.3f"%(alphamin) CWalpha = np.log10(np.logspace(alphamin, alphamax, npts+1)) CWm3 = ray.SubMach_TiTicri(ray.Ti_Ticri(CWm4, gam)/CWalpha, gam) CWpi3 = mf.Sigma_Mach(CWm3, gam)/mf.Sigma_Mach(M2, gam)/A3A2 CWpi4 = CWpi3*ray.Pi_Picri(CWm4, gam)/ray.Pi_Picri(CWm3, gam) CWm4 = np.ones(npts+1)*CWm4 plt.subplot(311) plt.plot(CWalpha, CWpi3, '-', color='#bb0000') plt.subplot(312)
