RocketConfigurationVisualizer/transportProps.txt at master · LiquidPropulsionGroup/RocketConfigurationVisualizer · GitHub

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         NASA-GLENN CHEMICAL EQUILIBRIUM PROGRAM CEA2, FEBRUARY 5, 2004
                   BY  BONNIE MCBRIDE AND SANFORD GORDON
      REFS: NASA RP-1311, PART I, 1994 AND NASA RP-1311, PART II, 1996

 *******************************************************************************


 ### CEA analysis performed on Sat 19-Dec-2020 01:44:34

 # Problem Type: "Rocket" (Finite Area Combustor)

 prob case=_______________8753 ro equilibrium frozen    fac

 !Contraction Ratio:
 ac/at=6.0489

 # Pressure (1 value):
 p,atm= 15
 # Chamber/Exit Pressure Ratio (1 value):
 pi/p= 15

 # Oxidizer/Fuel Wt. ratio (1 value):
 o/f= 2.3

 # You selected the following fuels and oxidizers:
 reac
 fuel RP-1              wt%=100.0000
 oxid O2(L)             wt%=100.0000

 # You selected these options for output:
 # short version of output
 output short
 # Proportions of any products will be expressed as Mass Fractions.
 output massf
 # Heat will be expressed as siunits
 output siunits
 # Transport properties calculated
 output transport


 # Input prepared by this script:prepareInputFile.cgi

 ### IMPORTANT:  The following line is the end of your CEA input file!
 end

              THEORETICAL ROCKET PERFORMANCE ASSUMING EQUILIBRIUM

            COMPOSITION DURING EXPANSION FROM FINITE AREA COMBUSTOR

 Pin =   220.4 PSIA
 Ac/At =  6.0489      Pinj/Pinf =  1.005538
 CASE = _______________

             REACTANT                    WT FRACTION      ENERGY      TEMP
                                          (SEE NOTE)     KJ/KG-MOL      K
 FUEL        RP-1                         1.0000000    -24717.700    298.150
 OXIDANT     O2(L)                        1.0000000    -12979.000     90.170

 O/F=    2.30000  %FUEL= 30.303030  R,EQ.RATIO= 1.480724  PHI,EQ.RATIO= 1.480724

                 INJECTOR  COMB END  THROAT     EXIT
 Pinj/P            1.0000   1.0112   1.7421   15.000
 P, BAR            15.199   15.031   8.7241   1.0132
 T, K             3389.10  3386.61  3214.84  2546.87
 RHO, KG/CU M    1.1837 0 1.1716 0 7.2596-1 1.1064-1
 H, KJ/KG         -818.62  -825.79 -1501.37 -3774.89
 U, KJ/KG        -2102.59 -2108.71 -2703.10 -4690.68
 G, KJ/KG        -41893.5 -41877.6 -40471.1 -34647.5
 S, KJ/(KG)(K)    12.1197  12.1218  12.1218  12.1218

 M, (1/n)          21.947   21.948   22.243   23.123
 (dLV/dLP)t      -1.03412 -1.03408 -1.02729 -1.00526
 (dLV/dLT)p        1.6245   1.6243   1.5272   1.1256
 Cp, KJ/(KG)(K)    6.4577   6.4589   5.9223   3.1296
 GAMMAs            1.1373   1.1372   1.1363   1.1632
 SON VEL,M/SEC     1208.4   1207.9   1168.5   1032.1
 MACH NUMBER        0.000    0.099    1.000    2.356

 TRANSPORT PROPERTIES (GASES ONLY)
   CONDUCTIVITY IN UNITS OF MILLIWATTS/(CM)(K)

 VISC,MILLIPOISE   1.0425   1.0420   1.0052  0.85452

  WITH EQUILIBRIUM REACTIONS

 Cp, KJ/(KG)(K)    6.4577   6.4589   5.9223   3.1296
 CONDUCTIVITY     15.3039  15.3016  13.5611   5.9260
 PRANDTL NUMBER    0.4399   0.4398   0.4390   0.4513

  WITH FROZEN REACTIONS

 Cp, KJ/(KG)(K)    2.0787   2.0785   2.0685   2.0135
 CONDUCTIVITY      3.4825   3.4802   3.3110   2.6592
 PRANDTL NUMBER    0.6223   0.6223   0.6280   0.6470

 PERFORMANCE PARAMETERS

 Ae/At                      6.0491   1.0000   3.1532
 CSTAR, M/SEC               1781.8   1781.8   1781.8
 CF                         0.0672   0.6558   1.3647
 Ivac, M/SEC               10837.8   2196.9   2808.2
 Isp, M/SEC                  119.7   1168.5   2431.6

 MASS FRACTIONS

 *CO              0.46625  0.46617  0.45701  0.42711
 *CO2             0.22159  0.22172  0.23614  0.28314
 COOH             0.00001  0.00001  0.00001  0.00000
 *H               0.00188  0.00187  0.00157  0.00048
 HCO              0.00002  0.00002  0.00001  0.00000
 HO2              0.00004  0.00004  0.00002  0.00000
 *H2              0.01118  0.01118  0.01103  0.01140
 H2O              0.24508  0.24513  0.25325  0.27187
 *O               0.00620  0.00618  0.00419  0.00025
 *OH              0.03599  0.03593  0.02837  0.00522
 *O2              0.01176  0.01174  0.00841  0.00054

  * THERMODYNAMIC PROPERTIES FITTED TO 20000.K

 NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS