## cea_compare2.py

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    from rocketcea.cea_obj import CEA_Obj
    from pylab import *

    Pc = 500.0
    eps = 25.0
    mrMin = 1.0
    mrStep = 0.05
    mrMax = 4.0

    mrL = [mrMin + i*mrStep for i in range( int((mrMax-mrMin)/mrStep))]
    ispLL = [] # a list of lists of Isp data

    for oxName,fuelName in [('N2O4','N2H4'),('N2O4','MMH'),('N2O4','M20'),
        ('CLF5','N2H4'),('CLF5','NH3')]:

        ispObj = CEA_Obj( oxName=oxName, fuelName=fuelName )

        ispL = [ispObj.get_Isp(Pc=Pc, MR=MR, eps=eps) for MR in mrL]
        ispLL.append( [max(ispL), '%s/%s'%(oxName,fuelName), ispL] )

    ispLL.sort(reverse=True) # sort in-place from high to low

    for maxIsp, name, ispL in ispLL:
        plot(mrL, ispL, label=name, linewidth=2)

    legend(loc='best')
    grid(True)
    title( 'Propellant Performance Comparison at Eps=%g, Pc=%g psia'%(eps,Pc) )
    xlabel( 'Mixture Ratio' )
    ylabel( 'Isp ODE (sec)' )
    savefig('cea_compare2.png', dpi=120)

    show()