Combustion of a solid rocket propellant using aluminum as fuel
reactants n 1. h 4. cl1. o 4. 72.06 -70690. s298.15 o c 1. h 1.86955o .031256s .008415 18.58 -2999.082l298.15 f al1. 9.00 0.0 s298.15 f mg1. o 1. 00 .20 s298.15 h 2. o 1. .16 -68317.4 l298.15 insert al2o3(l) namelists &inpt2 kase=50,hp=t,psia=t,p=500,250,125,50,5,trnspt=t,siunit=t&endDetonation of H_2/O_2 gases at stoichiometric conditions
reactants o 2. 00 100.0 0.0 g298.15 o h 2. 00 100. 0. g298.15 f namelists &inpt2 kase=52,detn=t,eratio=t,mix=1,t=298.15,500, p=1,trnspt=t, nodata=t&endCombustion of a liquid propellant combination at specified mixture ratio
reactants n 2. h 8. c 2. 50. 12734.8 l298.15 f .7861 n 2. h 4. 50. 12050. l298.15 f 1.0036 f 2. 100. -3098. l 85.02 o 1.505 namelists &inpt2 kase=122,p=1000,psia=t,of=t,mix=2.5,rkt=t,trnspt=t&end &rktinp pcp=10,68.0457, subar=10,5,3,2,1.5,1.1,1.01,1.001, supar=1.0005,1.05,1.1,1.5,1.8,2,5,10,100,200,500,1000&endConstant T,P problem (we generally don't use this in our applications) note that the ingredients are input in actual no. of moles
reactants si1. o 2. .01 m si3. n 4. .1 m mg1. f 2. .02 m n 2. 1. m namelists &inpt2 kase=200,tp=t,t=2173,2073,1973,1873,1773,p=1,trace=1.e-16&endAirbreather - combustion of hydrogen in air. also note the use of omit cards (normally we use these sparingly since we don't wish to limit the composition to a select few gases)
reactants h 2. 100. 0. g298.15 f n 1.56176o .419590ar.009324c .000300 100. -28.2 g298.15 o omit c2h4 c3o2 h2o(s) c(gr) omit c2n2 h2o(l) c2o c2h2 omit ho2 h2o2 omit nh2 ch2 ch nh3 omit c2n ch3 no2 ch4 omit hcn c2h c3 n2o omit n2c c2 cn hco omit n2h4 n2o4 cn2 namelists &inpt2 kase=950, tp=t,p=.1,.01,eratio=t,mix=1.5,1,2, t=3000,2000, trnspt=t&endInput deck for a shock-tube problem (gives the composition behind a shock wave)
reactants h 2. 00 0.050 m g 300.00 o 2. 00 0.050 m g 300.00 ar1. 00 0.900 m g 300.00 namelists &inpt2 kase=1207,p=10,20,mmhg=t, shock=t,trnspt=t&end &shkinp u1=1000,1100,1200,1250,1300,1350,1400,1450,1500,incdeq=t,incdfz=t&endConstant volume combustion such as that in an internal combustion engine....
reactants n 2. 00 .75524 g647.95 o o 2. 00 .23144 g647.95 o ar1. 00 .01286 g647.95 o c 1. o 2. 00 .00046 g647.95 o c 7. h 8. .4 2867. l 298.15 f c 8. h 18. .6 -59740. l 298.15 f namelists &inpt2 kase=1565,uv=t,v=300,225.24,of=t,mix=17,trace=1.e-15&endRocket combustion problem with the fuel being a nasty slurry of hydrazine and beryllium - exhaust products for this baby are highly toxic
reactants n 2. h 4. 80. 12050. l298.15 f 1.0036 be1. 20. 0.0 s298.15 f 1.85 h 2. o 2. 100. -44880. l298.15 o 1.407 insert beo(l) namelists &inpt2 kase=5612,fpct=t,mix=67,p=1000,500,psia=t,rkt=t&end &rktinp pcp=3,10,30,300, froz=f &endRocket example, this is set up to do combustion in the SSME (space shuttle main engine) with liquid oxygen and liquid hydrogen as propellants
reactants h 2. 100. -2154. l 20.27 f.0709 o 2. 100. -3102. l 90.18 o1.149 namelists &inpt2 kase=6666,p=3000,psia=t,fpct=t,mix=20,rkt=t ,trnspt=t&end &rktinp supar=1.5,2.5,4.,pcp=2.5,3,4,10,30,subar=2,3,10,nfz=4&end end