## cea_compare3.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 = 2.75

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

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

        ispArr = []
        MR = mrMin
        mrArr = []
        while MR < mrMax:
            ispArr.append( ispObj(Pc, MR, eps ))
            mrArr.append(MR)
            MR += mrStep
        plot(mrArr, ispArr, label='%s/%s'%(oxName,fuelName), 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_compare3.png', dpi=120)

    show()