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

         NASA-GLENN CHEMICAL EQUILIBRIUM PROGRAM CEA2, MAY 21, 2004
                   BY  BONNIE MCBRIDE AND SANFORD GORDON
      REFS: NASA RP-1311, PART I, 1994 AND NASA RP-1311, PART II, 1996

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



  
  prob case=_______________5312 ro equilibrium
  
  # Pressure (1 value):
  p,psia= 40
  # Supersonic Area Ratio (1 value):
  supar= 5
  
  # Oxidizer/Fuel Wt. ratio (20 values):
  o/f= 5,
  
  # You selected the following fuels and oxidizers:
  reac
  fuel H2                wt%=100.0000
  oxid O2                wt%=100.0000
  
  # You selected these options for output:
  # short version of output
  output short
  # Heat will be expressed as calories
  output calories
  # 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 INFINITE AREA COMBUSTOR

 Pin =    40.0 PSIA
 CASE = _______________

             REACTANT                    WT FRACTION      ENERGY      TEMP
                                          (SEE NOTE)      CAL/MOL       K  
 FUEL        H2                           1.0000000         0.000      0.000
 OXIDANT     O2                           1.0000000         0.000      0.000

 O/F=    5.00000  %FUEL= 16.666667  R,EQ.RATIO= 1.587337  PHI,EQ.RATIO= 1.587337

                 CHAMBER   THROAT     EXIT
 Pinf/P            1.0000   1.7274   27.843
 P, ATM            2.7218   1.5756  0.09776
 T, K             3083.15  2937.63  2179.38
 RHO, G/CC       1.2165-4 7.4918-5 6.5711-6
 H, CAL/G         0.00000  -287.21 -1493.27
 U, CAL/G         -541.82  -796.53 -1853.54
 G, CAL/G        -16248.7 -15769.1 -12979.0
 S, CAL/(G)(K)     5.2702   5.2702   5.2702

 M, (1/n)          11.308   11.462   12.021
 (dLV/dLP)t      -1.03604 -1.02873 -1.00310
 (dLV/dLT)p        1.7032   1.5869   1.0820
 Cp, CAL/(G)(K)    3.4161   3.0735   1.2776
 GAMMAs            1.1276   1.1278   1.1742
 SON VEL,M/SEC     1598.8   1550.3   1330.4
 MACH NUMBER        0.000    1.000    2.657

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

 VISC,MILLIPOISE  0.94122  0.90760  0.72263

  WITH EQUILIBRIUM REACTIONS

 Cp, CAL/(G)(K)    3.4161   3.0735   1.2776
 CONDUCTIVITY      7.1337   6.2737   1.8696
 PRANDTL NUMBER    0.4507   0.4446   0.4938

  WITH FROZEN REACTIONS

 Cp, CAL/(G)(K)    0.9855   0.9769   0.9152
 CONDUCTIVITY      1.3966   1.3246   0.9668
 PRANDTL NUMBER    0.6641   0.6694   0.6840

 PERFORMANCE PARAMETERS

 Ae/At                      1.0000   5.0000
 CSTAR, FT/SEC              7790.4   7790.4
 CF                         0.6529   1.4887
 Ivac,LB-SEC/LB              298.3    403.9
 Isp, LB-SEC/LB              158.1    360.5


 MOLE FRACTIONS

 *H               0.07147  0.06044  0.00962
 HO2              0.00001  0.00000  0.00000
 *H2              0.34261  0.34471  0.36428
 H2O              0.53522  0.55597  0.62354
 *O               0.00497  0.00332  0.00004
 *OH              0.04266  0.03344  0.00249
 *O2              0.00306  0.00212  0.00003

  * THERMODYNAMIC PROPERTIES FITTED TO 20000.K

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



  
