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from rocketcea.cea_obj import CEA_Obj
ispObj = CEA_Obj( oxName='LOX', fuelName='LH2')
s = ispObj.get_full_cea_output( Pc=[1000, 2000], # number or list of chamber pressures
MR=[6.0, 7.0], # number or list of mixture ratios
PcOvPe=[100,200],# number or list of Pc/Pexit
eps=[40.0,60], # number or list of supersonic area ratios
subar=[3,2], # number or list of subsonic area ratios
short_output=0, # 0 or 1 to control output length
pc_units='psia', # pc_units = 'psia', 'bar', 'atm', 'mmh'
output='siunits',# output = 'calories' or 'siunits'
fac_CR=None) # finite area combustor, contraction ratio
print( s )
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