.. new_propellants .. _`new_propellants_link`: New Propellants =============== New propellants can be added and existing propellants modified. Create a python string variable that contains the new card. It can be multiline such as:: card_str = """ oxid N2O4(L) N 2 O 4 wt%=96.5 h,cal=-4676.0 t(k)=298.15 oxid SiO2 Si 1.0 O 2.0 wt%=3.5 h,cal=-216000.0 t(k)=298.15 rho=1.48 """ Add the new propellant card to RocketCEA and give it a name. It can be added as oxidizer, fuel or propellant.:: add_new_oxidizer( 'GelN2O4', card_str ) add_new_fuel( 'MMH_AL', card_str ) add_new_propellant( 'MyProp', card_str ) New Ox and Fuel --------------- The example below defines some gel propellants, adding SiO2 to the oxidizer and Al to the fuel. .. literalinclude:: ./_static/example_scripts/new_propellants.py Outputs:: ******************************************************************************* NASA-GLENN CHEMICAL EQUILIBRIUM PROGRAM CEA, OCTOBER 18, 2002 BY BONNIE MCBRIDE AND SANFORD GORDON REFS: NASA RP-1311, PART I, 1994 AND NASA RP-1311, PART II, 1996 ******************************************************************************* reac fuel CH6N2(L) C 1.0 H 6.0 N 2.0 wt%=60.00 h,cal=12900.0 t(k)=298.15 rho=.874 fuel AL AL 1.0 wt%=40.00 h,cal=0.0 t(k)=298.15 rho=0.1 oxid N2O4(L) N 2 O 4 wt%=96.5 h,cal=-4676.0 t(k)=298.15 oxid SiO2 Si 1.0 O 2.0 wt%=3.5 h,cal=-216000.0 t(k)=298.15 rho=1.48 prob case=GelN2O4_/_MMH_AL rocket equilibrium p,psia=1850.000000, supar=40.000000, o/f=0.700000 outp calories short end THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 1850.0 PSIA CASE = GelN2O4_/_MMH_A REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) CAL/MOL K FUEL CH6N2(L) 0.6000000 12900.000 298.150 FUEL AL 0.4000000 0.000 298.150 OXIDANT N2O4(L) 0.9650000 -4676.000 298.150 OXIDANT SiO2 0.0350000 -216000.000 298.150 REACTANT DENSITY= 42.2857 G/CC O/F= 0.70000 %FUEL= 58.823529 R,EQ.RATIO= 2.921279 PHI,EQ.RATIO= 2.974634 CHAMBER THROAT EXIT Pinf/P 1.0000 1.7251 363.79 P, ATM 125.88 72.973 0.34604 T, K 3082.43 2905.55 1698.41 RHO, G/CC 1.1177-2 6.9501-3 6.0631-5 H, CAL/G 26.820 -116.52 -1150.32 U, CAL/G -245.95 -370.79 -1288.54 G, CAL/G -7686.58 -7387.30 -5400.38 S, CAL/(G)(K) 2.5024 2.5024 2.5024 M, (1/n) 22.457 22.708 24.419 MW, MOL WT 21.109 21.154 21.314 (dLV/dLP)t -1.01858 -1.08537 -1.07583 (dLV/dLT)p 1.2354 2.3383 2.8119 Cp, CAL/(G)(K) 0.8362 2.4115 4.0182 GAMMAs 1.1668 1.1275 1.0921 SON VEL,M/SEC 1153.9 1095.2 794.7 MACH NUMBER 0.000 1.000 3.949 PERFORMANCE PARAMETERS Ae/At 1.0000 40.000 CSTAR, FT/SEC 5497.8 5497.8 CF 0.6536 1.8729 Ivac,LB-SEC/LB 210.7 338.8 Isp, LB-SEC/LB 111.7 320.0 MOLE FRACTIONS *AL 0.00600 0.00518 0.00000 ALH 0.00437 0.00353 0.00000 ALH2 0.00006 0.00003 0.00000 ALH3 0.00002 0.00001 0.00000 ALN 0.00001 0.00001 0.00000 *ALO 0.00007 0.00003 0.00000 ALOH 0.00979 0.00662 0.00000 AL(OH)2 0.00001 0.00000 0.00000 AL2 0.00005 0.00003 0.00000 AL2O 0.02172 0.01895 0.00000 AL2O2 0.00006 0.00003 0.00000 CH3 0.00004 0.00004 0.00000 CH4 0.00011 0.00012 0.00011 *CN 0.00001 0.00001 0.00000 *CO 0.15623 0.15626 0.14630 *CO2 0.00007 0.00004 0.00000 C2H2,acetylene 0.00009 0.00012 0.00004 *H 0.01187 0.00904 0.00016 HCN 0.00423 0.00459 0.00142 HCO 0.00002 0.00001 0.00000 HNC 0.00079 0.00074 0.00004 *H2 0.46728 0.47240 0.48876 H2O 0.00153 0.00083 0.00001 NH2 0.00002 0.00001 0.00000 NH3 0.00014 0.00009 0.00000 *N2 0.25026 0.24773 0.23571 *OH 0.00001 0.00001 0.00000 *Si 0.00003 0.00003 0.00000 SiH 0.00004 0.00004 0.00000 SiH2 0.00001 0.00001 0.00000 SiO 0.00497 0.00499 0.00028 ALN(cr) 0.00000 0.00000 0.03294 ALN(L) 0.00000 0.00589 0.00000 AL2O3(a) 0.00000 0.00000 0.07646 AL2O3(L) 0.06004 0.06257 0.00000 C(gr) 0.00000 0.00000 0.01534 Si2N2O(cr) 0.00000 0.00000 0.00242 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS New Monoprop ------------ .. literalinclude:: ./_static/example_scripts/new_propellants_2.py Outputs:: ******************************************************************************* NASA-GLENN CHEMICAL EQUILIBRIUM PROGRAM CEA, OCTOBER 18, 2002 BY BONNIE MCBRIDE AND SANFORD GORDON REFS: NASA RP-1311, PART I, 1994 AND NASA RP-1311, PART II, 1996 ******************************************************************************* reac name H2O2(L) H 2 O 2 wt%=100.00 h,cal=-44880.0 t(k)=298.15 rho.g/cc=1.407 prob case= MyProp rocket equilibrium p,psia=250.000000, supar=40.000000, outp calories short end THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM COMPOSITION DURING EXPANSION FROM INFINITE AREA COMBUSTOR Pinj = 250.0 PSIA CASE = MyProp REACTANT WT FRACTION ENERGY TEMP (SEE NOTE) CAL/MOL K NAME H2O2(L) 1.0000000 -44880.000 298.150 REACTANT DENSITY= 1.4070 G/CC O/F= 0.00000 %FUEL= 0.000000 R,EQ.RATIO= 0.500000 PHI,EQ.RATIO= 0.000000 CHAMBER THROAT EXIT Pinf/P 1.0000 1.8080 718.01 P, ATM 17.011 9.4092 0.02369 T, K 1274.61 1130.86 287.09 RHO, G/CC 3.6882-3 2.2993-3 2.3038-5 H, CAL/G -1319.43 -1381.79 -1707.68 U, CAL/G -1431.13 -1480.90 -1732.58 G, CAL/G -4379.64 -4096.87 -2396.94 S, CAL/(G)(K) 2.4009 2.4009 2.4009 M, (1/n) 22.676 22.676 22.907 MW, MOL WT 22.676 22.676 22.676 (dLV/dLP)t -1.00000 -1.00000 -2.96976 (dLV/dLT)p 1.0001 1.0000 37.6942 Cp, CAL/(G)(K) 0.4410 0.4265 59.6427 GAMMAs 1.2480 1.2586 1.1073 SON VEL,M/SEC 763.7 722.4 339.7 MACH NUMBER 0.000 1.000 5.306 PERFORMANCE PARAMETERS Ae/At 1.0000 40.000 CSTAR, FT/SEC 3404.6 3404.6 CF 0.6961 1.7369 Ivac,LB-SEC/LB 132.2 189.7 Isp, LB-SEC/LB 73.7 183.8 MOLE FRACTIONS H2O 0.66666 0.66667 0.65659 *OH 0.00001 0.00000 0.00000 *O2 0.33333 0.33333 0.33333 H2O(L) 0.00000 0.00000 0.01008 * THERMODYNAMIC PROPERTIES FITTED TO 20000.K NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS