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1988-01-22
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HYDROGEN/FLUORINE ROCKET ENGINE ANALYSIS PROGRAM
Version 1.01
(c) December, 1987
Software Package by Kerry Hicks, MS
Analysis of Rl10A-3-1 (Using Fluorine)
Study Initiated on 01-22-1988 at 17:35:31
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.1889E+00 SQUARE FEET
AREA OF NOZZLE EXIT 0.7558E+01 SQUARE FEET
AREA RATIO: 40.01 : 1
CHAMBER PRESSURE 0.2041E+02 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 5.000 : 1.000
ADIABATIC FLAME TEMPERATURE: 2994.9 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=2994.92 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2707E+01 X=0.5411E+00
Diatomic Fluorine N=0.2363E-09 X=0.4724E-10
Hydrogen Fluoride N=0.1999E+01 X=0.3997E+00
Monatomic Hydrogen N=0.2958E+00 X=0.5912E-01
Monatomic Fluorine N=0.6125E-03 X=0.1224E-03
Total N=0.5003E+01
Molecular Weight of Mixture=0.9148E+01
Qin=+1.1417E+02 kcal
Qout=+1.1414E+02 kcal
Qnet=+2.9381E-02 kcal
P=0.2041E+02 atm
S=0.4772E+02 cal/(mole K)
Ratio of specific heats: 1.303
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.354
Mass flow rate (mdot): 0.3283E+02 lbm/sec.
Pressure at exit: 0.2331E-01 atm. (0.3426E+00 psia)
Temperature at exit: 509.45 Kelvin
Exit velocity: 0.1364E+05 ft/sec.
Thrust at sea-level: -1.7059E+03 lbf.
(Negative thrust -- out of the engine's operating range.)
Thrust at 10,000 ft: +3.2886E+03 lbf.
Thrust at 25,000 ft: +8.3533E+03 lbf.
Thrust at 50,000 ft: +1.2458E+04 lbf.
Thrust at 75,000 ft: +1.3732E+04 lbf.
Thrust at 100,000 ft: +1.4119E+04 lbf.
Thrust at 150,000 ft: +1.4266E+04 lbf.
Thrust in a vacuum: +1.4289E+04 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Study ABORTED on 01-22-1988 at 17:36:30
Analysis of OOS-AJ (Using Fluorine)
Study Initiated on 01-22-1988 at 17:37:31
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.4590E-01 SQUARE FEET
AREA OF NOZZLE EXIT 0.1331E+02 SQUARE FEET
AREA RATIO: 289.98 : 1
CHAMBER PRESSURE 0.1225E+03 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 6.000 : 1.000
ADIABATIC FLAME TEMPERATURE: 3304.1 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3304.12 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2091E+01 X=0.4724E+00
Diatomic Fluorine N=0.2494E-08 X=0.5633E-09
Hydrogen Fluoride N=0.1999E+01 X=0.4515E+00
Monatomic Hydrogen N=0.3359E+00 X=0.7586E-01
Monatomic Fluorine N=0.1052E-02 X=0.2377E-03
Total N=0.4427E+01
Molecular Weight of Mixture=0.1007E+02
Qin=+1.1205E+02 kcal
Qout=+1.1201E+02 kcal
Qnet=+3.5362E-02 kcal
P=0.1225E+03 atm
S=0.4543E+02 cal/(mole K)
Ratio of specific heats: 1.301
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.356
Mass flow rate (mdot): 0.4783E+02 lbm/sec.
Pressure at exit: 0.8841E-02 atm. (0.1299E+00 psia)
Temperature at exit: 270.03 Kelvin
Exit velocity: 0.1433E+05 ft/sec.
Thrust at sea-level: -6.6055E+03 lbf.
(Negative thrust -- out of the engine's operating range.)
Thrust at 10,000 ft: +2.1901E+03 lbf.
Thrust at 25,000 ft: +1.1109E+04 lbf.
Thrust at 50,000 ft: +1.8338E+04 lbf.
Thrust at 75,000 ft: +2.0582E+04 lbf.
Thrust at 100,000 ft: +2.1263E+04 lbf.
Thrust at 150,000 ft: +2.1522E+04 lbf.
Thrust in a vacuum: +2.1561E+04 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Numerical Difficulties Encountered -- Not Calculated.
Normal Termination on 01-22-1988 at 17:38:03
Analysis of ASE-PW (Using Fluorine)
Study Initiated on 01-22-1988 at 17:38:51
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.3773E-01 SQUARE FEET
AREA OF NOZZLE EXIT 0.1509E+02 SQUARE FEET
AREA RATIO: 399.95 : 1
CHAMBER PRESSURE 0.1306E+03 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 6.000 : 1.000
ADIABATIC FLAME TEMPERATURE: 3307.3 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3307.33 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2093E+01 X=0.4728E+00
Diatomic Fluorine N=0.2535E-08 X=0.5727E-09
Hydrogen Fluoride N=0.1999E+01 X=0.4516E+00
Monatomic Hydrogen N=0.3336E+00 X=0.7537E-01
Monatomic Fluorine N=0.1031E-02 X=0.2328E-03
Total N=0.4426E+01
Molecular Weight of Mixture=0.1007E+02
Qin=+1.1216E+02 kcal
Qout=+1.1213E+02 kcal
Qnet=+3.2288E-02 kcal
P=0.1306E+03 atm
S=-.3220E+04 cal/(mole K)
Ratio of specific heats: 1.301
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.357
Mass flow rate (mdot): 0.4191E+02 lbm/sec.
Pressure at exit: 0.6037E-02 atm. (0.8872E-01 psia)
Temperature at exit: 239.80 Kelvin
Exit velocity: 0.1440E+05 ft/sec.
Thrust at sea-level: -1.2977E+04 lbf.
(Negative thrust -- out of the engine's operating range.)
Thrust at 10,000 ft: -3.0056E+03 lbf.
(Negative thrust -- out of the engine's operating range.)
Thrust at 25,000 ft: +7.1062E+03 lbf.
Thrust at 50,000 ft: +1.5302E+04 lbf.
Thrust at 75,000 ft: +1.7846E+04 lbf.
Thrust at 100,000 ft: +1.8618E+04 lbf.
Thrust at 150,000 ft: +1.8911E+04 lbf.
Thrust in a vacuum: +1.8956E+04 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Numerical Difficulties Encountered -- Not Calculated.
Normal Termination on 01-22-1988 at 17:39:20
Analysis of AMPT (Using Fluorine)
Study Initiated on 01-22-1988 at 17:39:48
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.9083E-01 SQUARE FEET
AREA OF NOZZLE EXIT 0.1817E+02 SQUARE FEET
AREA RATIO: 200.04 : 1
CHAMBER PRESSURE 0.6805E+02 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 5.500 : 1.000
ADIABATIC FLAME TEMPERATURE: 3163.3 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3163.27 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2376E+01 X=0.5070E+00
Diatomic Fluorine N=0.8639E-09 X=0.1844E-09
Hydrogen Fluoride N=0.1999E+01 X=0.4266E+00
Monatomic Hydrogen N=0.3104E+00 X=0.6623E-01
Monatomic Fluorine N=0.7453E-03 X=0.1590E-03
Total N=0.4686E+01
Molecular Weight of Mixture=0.9627E+01
Qin=+1.1339E+02 kcal
Qout=+1.1337E+02 kcal
Qnet=+2.0889E-02 kcal
P=0.6805E+02 atm
S=-.2698E+04 cal/(mole K)
Ratio of specific heats: 1.301
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.355
Mass flow rate (mdot): 0.5255E+02 lbm/sec.
Pressure at exit: 0.8230E-02 atm. (0.1209E+00 psia)
Temperature at exit: 297.13 Kelvin
Exit velocity: 0.1426E+05 ft/sec.
Thrust at sea-level: -1.4850E+04 lbf.
(Negative thrust -- out of the engine's operating range.)
Thrust at 10,000 ft: -2.8426E+03 lbf.
(Negative thrust -- out of the engine's operating range.)
Thrust at 25,000 ft: +9.3331E+03 lbf.
Thrust at 50,000 ft: +1.9201E+04 lbf.
Thrust at 75,000 ft: +2.2265E+04 lbf.
Thrust at 100,000 ft: +2.3195E+04 lbf.
Thrust at 150,000 ft: +2.3547E+04 lbf.
Thrust in a vacuum: +2.3602E+04 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Numerical Difficulties Encountered -- Not Calculated.
Normal Termination on 01-22-1988 at 17:41:08
Analysis of OOS-PW (Using Fluorine)
Study Initiated on 01-22-1988 at 17:41:50
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.4589E-01 SQUARE FEET
AREA OF NOZZLE EXIT 0.1147E+02 SQUARE FEET
AREA RATIO: 249.95 : 1
CHAMBER PRESSURE 0.1293E+03 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 6.000 : 1.000
ADIABATIC FLAME TEMPERATURE: 3306.8 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3306.83 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2092E+01 X=0.4727E+00
Diatomic Fluorine N=0.2528E-08 X=0.5712E-09
Hydrogen Fluoride N=0.1999E+01 X=0.4516E+00
Monatomic Hydrogen N=0.3340E+00 X=0.7545E-01
Monatomic Fluorine N=0.1034E-02 X=0.2336E-03
Total N=0.4426E+01
Molecular Weight of Mixture=0.1007E+02
Qin=+1.1215E+02 kcal
Qout=+1.1211E+02 kcal
Qnet=+3.2379E-02 kcal
P=0.1293E+03 atm
S=-.3360E+04 cal/(mole K)
Ratio of specific heats: 1.301
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.356
Mass flow rate (mdot): 0.5046E+02 lbm/sec.
Pressure at exit: 0.1147E-01 atm. (0.1686E+00 psia)
Temperature at exit: 285.72 Kelvin
Exit velocity: 0.1431E+05 ft/sec.
Thrust at sea-level: -1.5564E+03 lbf.
(Negative thrust -- out of the engine's operating range.)
Thrust at 10,000 ft: +6.0233E+03 lbf.
Thrust at 25,000 ft: +1.3709E+04 lbf.
Thrust at 50,000 ft: +1.9939E+04 lbf.
Thrust at 75,000 ft: +2.1873E+04 lbf.
Thrust at 100,000 ft: +2.2460E+04 lbf.
Thrust at 150,000 ft: +2.2682E+04 lbf.
Thrust in a vacuum: +2.2717E+04 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Numerical Difficulties Encountered -- Not Calculated.
Normal Termination on 01-22-1988 at 17:42:18
Analysis of SSME (mod.1) (Using Fluorine)
Study Initiated on 01-22-1988 at 17:43:03
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.5792E+00 SQUARE FEET
AREA OF NOZZLE EXIT 0.4487E+02 SQUARE FEET
AREA RATIO: 77.47 : 1
CHAMBER PRESSURE 0.2049E+03 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 6.021 : 1.000
ADIABATIC FLAME TEMPERATURE: 3334.9 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3334.91 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2089E+01 X=0.4738E+00
Diatomic Fluorine N=0.2953E-08 X=0.6700E-09
Hydrogen Fluoride N=0.1999E+01 X=0.4535E+00
Monatomic Hydrogen N=0.3196E+00 X=0.7250E-01
Monatomic Fluorine N=0.9091E-03 X=0.2062E-03
Total N=0.4408E+01
Molecular Weight of Mixture=0.1010E+02
Qin=+1.1289E+02 kcal
Qout=+1.1287E+02 kcal
Qnet=+1.4984E-02 kcal
P=0.2049E+03 atm
S=-.3595E+04 cal/(mole K)
Ratio of specific heats: 1.300
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.354
Mass flow rate (mdot): 0.1006E+04 lbm/sec.
Pressure at exit: 0.9286E-01 atm. (0.1365E+01 psia)
Temperature at exit: 445.31 Kelvin
Exit velocity: 0.1399E+05 ft/sec.
Thrust at sea-level: +3.5152E+05 lbf.
Thrust at 10,000 ft: +3.8117E+05 lbf.
Thrust at 25,000 ft: +4.1124E+05 lbf.
Thrust at 50,000 ft: +4.3560E+05 lbf.
Thrust at 75,000 ft: +4.4317E+05 lbf.
Thrust at 100,000 ft: +4.4547E+05 lbf.
Thrust at 150,000 ft: +4.4634E+05 lbf.
Thrust in a vacuum: +4.4647E+05 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Numerical Difficulties Encountered -- Not Calculated.
Normal Termination on 01-22-1988 at 17:43:55
Analysis of SSME (mod. 2) (Using Fluorine)
Study Initiated on 01-22-1988 at 17:44:42
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.5749E+00 SQUARE FEET
AREA OF NOZZLE EXIT 0.4456E+02 SQUARE FEET
AREA RATIO: 77.51 : 1
CHAMBER PRESSURE 0.2021E+03 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 6.000 : 1.000
ADIABATIC FLAME TEMPERATURE: 3329.7 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3329.69 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2100E+01 X=0.4753E+00
Diatomic Fluorine N=0.2853E-08 X=0.6456E-09
Hydrogen Fluoride N=0.1999E+01 X=0.4525E+00
Monatomic Hydrogen N=0.3183E+00 X=0.7205E-01
Monatomic Fluorine N=0.8963E-03 X=0.2029E-03
Total N=0.4418E+01
Molecular Weight of Mixture=0.1009E+02
Qin=+1.1296E+02 kcal
Qout=+1.1294E+02 kcal
Qnet=+1.9424E-02 kcal
P=0.2021E+03 atm
S=-.3572E+04 cal/(mole K)
Ratio of specific heats: 1.300
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.354
Mass flow rate (mdot): 0.9851E+03 lbm/sec.
Pressure at exit: 0.9154E-01 atm. (0.1345E+01 psia)
Temperature at exit: 444.62 Kelvin
Exit velocity: 0.1399E+05 ft/sec.
Thrust at sea-level: +3.4281E+05 lbf.
Thrust at 10,000 ft: +3.7226E+05 lbf.
Thrust at 25,000 ft: +4.0212E+05 lbf.
Thrust at 50,000 ft: +4.2632E+05 lbf.
Thrust at 75,000 ft: +4.3383E+05 lbf.
Thrust at 100,000 ft: +4.3612E+05 lbf.
Thrust at 150,000 ft: +4.3698E+05 lbf.
Thrust in a vacuum: +4.3711E+05 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Numerical Difficulties Encountered -- Not Calculated.
Normal Termination on 01-22-1988 at 17:45:10
Analysis of J-2 (Using Fluorine)
Study Initiated on 01-22-1988 at 17:45:47
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.1178E+01 SQUARE FEET
AREA OF NOZZLE EXIT 0.3239E+02 SQUARE FEET
AREA RATIO: 27.50 : 1
CHAMBER PRESSURE 0.5308E+02 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 5.500 : 1.000
ADIABATIC FLAME TEMPERATURE: 3151.4 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3151.44 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2371E+01 X=0.5055E+00
Diatomic Fluorine N=0.7983E-09 X=0.1702E-09
Hydrogen Fluoride N=0.1999E+01 X=0.4262E+00
Monatomic Hydrogen N=0.3193E+00 X=0.6807E-01
Monatomic Fluorine N=0.8017E-03 X=0.1709E-03
Total N=0.4690E+01
Molecular Weight of Mixture=0.9618E+01
Qin=+1.1293E+02 kcal
Qout=+1.1290E+02 kcal
Qnet=+2.9762E-02 kcal
P=0.5308E+02 atm
S=-.2485E+04 cal/(mole K)
Ratio of specific heats: 1.302
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.352
Mass flow rate (mdot): 0.5319E+03 lbm/sec.
Pressure at exit: 0.1035E+00 atm. (0.1520E+01 psia)
Temperature at exit: 619.84 Kelvin
Exit velocity: 0.1345E+05 ft/sec.
Thrust at sea-level: +1.6087E+05 lbf.
Thrust at 10,000 ft: +1.8227E+05 lbf.
Thrust at 25,000 ft: +2.0398E+05 lbf.
Thrust at 50,000 ft: +2.2157E+05 lbf.
Thrust at 75,000 ft: +2.2703E+05 lbf.
Thrust at 100,000 ft: +2.2869E+05 lbf.
Thrust at 150,000 ft: +2.2932E+05 lbf.
Thrust in a vacuum: +2.2941E+05 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Study ABORTED on 01-22-1988 at 17:46:49
Analysis of J-2S (Using Fluorine)
Study Initiated on 01-22-1988 at 17:47:16
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.8118E+00 SQUARE FEET
AREA OF NOZZLE EXIT 0.3216E+02 SQUARE FEET
AREA RATIO: 39.62 : 1
CHAMBER PRESSURE 0.8165E+02 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 5.500 : 1.000
ADIABATIC FLAME TEMPERATURE: 3172.2 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3172.18 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2379E+01 X=0.5080E+00
Diatomic Fluorine N=0.9199E-09 X=0.1964E-09
Hydrogen Fluoride N=0.1999E+01 X=0.4269E+00
Monatomic Hydrogen N=0.3040E+00 X=0.6492E-01
Monatomic Fluorine N=0.7083E-03 X=0.1512E-03
Total N=0.4683E+01
Molecular Weight of Mixture=0.9633E+01
Qin=+1.1373E+02 kcal
Qout=+1.1370E+02 kcal
Qnet=+3.4874E-02 kcal
P=0.8165E+02 atm
S=0.4577E+02 cal/(mole K)
Ratio of specific heats: 1.301
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.353
Mass flow rate (mdot): 0.5625E+03 lbm/sec.
Pressure at exit: 0.9492E-01 atm. (0.1395E+01 psia)
Temperature at exit: 544.05 Kelvin
Exit velocity: 0.1368E+05 ft/sec.
Thrust at sea-level: +1.7762E+05 lbf.
Thrust at 10,000 ft: +1.9888E+05 lbf.
Thrust at 25,000 ft: +2.2043E+05 lbf.
Thrust at 50,000 ft: +2.3789E+05 lbf.
Thrust at 75,000 ft: +2.4331E+05 lbf.
Thrust at 100,000 ft: +2.4496E+05 lbf.
Thrust at 150,000 ft: +2.4558E+05 lbf.
Thrust in a vacuum: +2.4568E+05 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Study ABORTED on 01-22-1988 at 17:48:15
Analysis of RL10A-3-3 (Using Fluorine)
Study Initiated on 01-22-1988 at 17:48:44
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.1400E+00 SQUARE FEET
AREA OF NOZZLE EXIT 0.7994E+01 SQUARE FEET
AREA RATIO: 57.10 : 1
CHAMBER PRESSURE 0.2722E+02 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 5.000 : 1.000
ADIABATIC FLAME TEMPERATURE: 3006.5 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3006.49 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2713E+01 X=0.5428E+00
Diatomic Fluorine N=0.2567E-09 X=0.5135E-10
Hydrogen Fluoride N=0.1999E+01 X=0.3999E+00
Monatomic Hydrogen N=0.2859E+00 X=0.5718E-01
Monatomic Fluorine N=0.5598E-03 X=0.1120E-03
Total N=0.4999E+01
Molecular Weight of Mixture=0.9155E+01
Qin=+1.1466E+02 kcal
Qout=+1.1466E+02 kcal
Qnet=-3.5858E-04 kcal
P=0.2722E+02 atm
S=0.4716E+02 cal/(mole K)
Ratio of specific heats: 1.302
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.354
Mass flow rate (mdot): 0.3240E+02 lbm/sec.
Pressure at exit: 0.1887E-01 atm. (0.2774E+00 psia)
Temperature at exit: 448.51 Kelvin
Exit velocity: 0.1383E+05 ft/sec.
Thrust at sea-level: -2.6730E+03 lbf.
(Negative thrust -- out of the engine's operating range.)
Thrust at 10,000 ft: +2.6096E+03 lbf.
Thrust at 25,000 ft: +7.9664E+03 lbf.
Thrust at 50,000 ft: +1.2308E+04 lbf.
Thrust at 75,000 ft: +1.3656E+04 lbf.
Thrust at 100,000 ft: +1.4065E+04 lbf.
Thrust at 150,000 ft: +1.4220E+04 lbf.
Thrust in a vacuum: +1.4244E+04 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Numerical Difficulties Encountered -- Not Calculated.
Normal Termination on 01-22-1988 at 17:49:01
Analysis of XLR129-P-1 (skirt contracted) (Using Fluorine)
Study Initiated on 01-22-1988 at 17:50:19
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.3203E+00 SQUARE FEET
AREA OF NOZZLE EXIT 0.1121E+02 SQUARE FEET
AREA RATIO: 35.00 : 1
CHAMBER PRESSURE 0.1864E+03 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 5.000 : 1.000
ADIABATIC FLAME TEMPERATURE: 3085.0 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3084.97 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2743E+01 X=0.5520E+00
Diatomic Fluorine N=0.4426E-09 X=0.8907E-10
Hydrogen Fluoride N=0.2000E+01 X=0.4025E+00
Monatomic Hydrogen N=0.2258E+00 X=0.4545E-01
Monatomic Fluorine N=0.3056E-03 X=0.6150E-04
Total N=0.4968E+01
Molecular Weight of Mixture=0.9212E+01
Qin=+1.1784E+02 kcal
Qout=+1.1781E+02 kcal
Qnet=+3.4767E-02 kcal
P=0.1864E+03 atm
S=-.3937E+04 cal/(mole K)
Ratio of specific heats: 1.299
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.350
Mass flow rate (mdot): 0.5021E+03 lbm/sec.
Pressure at exit: 0.2607E+00 atm. (0.3831E+01 psia)
Temperature at exit: 560.89 Kelvin
Exit velocity: 0.1375E+05 ft/sec.
Thrust at sea-level: +1.9707E+05 lbf.
Thrust at 10,000 ft: +2.0448E+05 lbf.
Thrust at 25,000 ft: +2.1199E+05 lbf.
Thrust at 50,000 ft: +2.1808E+05 lbf.
Thrust at 75,000 ft: +2.1997E+05 lbf.
Thrust at 100,000 ft: +2.2054E+05 lbf.
Thrust at 150,000 ft: +2.2076E+05 lbf.
Thrust in a vacuum: +2.2079E+05 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Study ABORTED on 01-22-1988 at 17:51:19
Analysis of XLR129-P-1 (skirt extended) (Using Fluorine)
Study Initiated on 01-22-1988 at 17:51:57
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.3203E+00 SQUARE FEET
AREA OF NOZZLE EXIT 0.2402E+02 SQUARE FEET
AREA RATIO: 74.99 : 1
CHAMBER PRESSURE 0.1864E+03 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 5.000 : 1.000
ADIABATIC FLAME TEMPERATURE: 3085.0 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3084.97 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2743E+01 X=0.5520E+00
Diatomic Fluorine N=0.4426E-09 X=0.8907E-10
Hydrogen Fluoride N=0.2000E+01 X=0.4025E+00
Monatomic Hydrogen N=0.2258E+00 X=0.4545E-01
Monatomic Fluorine N=0.3056E-03 X=0.6150E-04
Total N=0.4968E+01
Molecular Weight of Mixture=0.9212E+01
Qin=+1.1784E+02 kcal
Qout=+1.1781E+02 kcal
Qnet=+3.4767E-02 kcal
P=0.1864E+03 atm
S=0.4370E+02 cal/(mole K)
Ratio of specific heats: 1.299
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.352
Mass flow rate (mdot): 0.5023E+03 lbm/sec.
Pressure at exit: 0.8933E-01 atm. (0.1313E+01 psia)
Temperature at exit: 422.16 Kelvin
Exit velocity: 0.1410E+05 ft/sec.
Thrust at sea-level: +1.7387E+05 lbf.
Thrust at 10,000 ft: +1.8975E+05 lbf.
Thrust at 25,000 ft: +2.0584E+05 lbf.
Thrust at 50,000 ft: +2.1889E+05 lbf.
Thrust at 75,000 ft: +2.2294E+05 lbf.
Thrust at 100,000 ft: +2.2417E+05 lbf.
Thrust at 150,000 ft: +2.2463E+05 lbf.
Thrust in a vacuum: +2.2470E+05 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
Numerical Difficulties Encountered -- Not Calculated.
Normal Termination on 01-22-1988 at 17:52:20
Analysis of SUZEQ Fluorine Engine
Study Initiated on 01-22-1988 at 17:56:33
ENGINE SPECS:
-------------
AREA OF NOZZLE THROAT 0.1000E+01 SQUARE FEET
AREA OF NOZZLE EXIT 0.1000E+02 SQUARE FEET
AREA RATIO: 10.00 : 1
CHAMBER PRESSURE 0.2700E+02 ATM
FLUORINE TO HYDROGEN MASS FLOW RATE: 6.000 : 1.000
ADIABATIC FLAME TEMPERATURE: 3224.0 Kelvin
********** COMBUSTION CHAMBER DETAILS ***********
--------------------------
Temperature=3223.99 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2055E+01 X=0.4621E+00
Diatomic Fluorine N=0.1502E-08 X=0.3377E-09
Hydrogen Fluoride N=0.1998E+01 X=0.4493E+00
Monatomic Hydrogen N=0.3926E+00 X=0.8828E-01
Monatomic Fluorine N=0.1615E-02 X=0.3630E-03
Total N=0.4448E+01
Molecular Weight of Mixture=0.1002E+02
Qin=+1.0897E+02 kcal
Qout=+1.0901E+02 kcal
Qnet=-3.8002E-02 kcal
P=0.2700E+02 atm
S=0.4807E+02 cal/(mole K)
Ratio of specific heats: 1.304
*********** FROZEN FLOW CALCULATIONS **********
------------------------
Average ratio of specific heats: 1.347
Mass flow rate (mdot): 0.2314E+03 lbm/sec.
Pressure at exit: 0.2272E+00 atm. (0.3339E+01 psia)
Temperature at exit: 941.15 Kelvin
Exit velocity: 0.1258E+05 ft/sec.
Thrust at sea-level: +7.4155E+04 lbf.
Thrust at 10,000 ft: +8.0763E+04 lbf.
Thrust at 25,000 ft: +8.7464E+04 lbf.
Thrust at 50,000 ft: +9.2895E+04 lbf.
Thrust at 75,000 ft: +9.4581E+04 lbf.
Thrust at 100,000 ft: +9.5093E+04 lbf.
Thrust at 150,000 ft: +9.5287E+04 lbf.
Thrust in a vacuum: +9.5317E+04 lbf.
********** EQUILIBRIUM FLOW CALCULATIONS **********
-----------------------------
EQUILIBRIUM FLOW EXIT PROPERTIES:
Temperature=1379.71 Kelvin
Reaction Equation Coefficients and Mole Fractions:
Diatomic Hydrogen N=0.2142E+01 X=0.5171E+00
Diatomic Fluorine N=0.7711E-21 X=0.1862E-21
Hydrogen Fluoride N=0.2000E+01 X=0.4829E+00
Monatomic Hydrogen N=0.5472E-05 X=0.1321E-05
Monatomic Fluorine N=0.1729E-10 X=0.4174E-11
Total N=0.4142E+01
Molecular Weight of Mixture=0.1070E+02
Qin=+4.1659E+01 kcal
Qout=+1.2960E+02 kcal
Qnet=-8.7940E+01 kcal
P=0.2272E+00 atm
S=0.5137E+02 cal/(mole K)
Average ratio of specific heats: 1.347
Mass flow rate (mdot): 0.2314E+03 lbm/sec.
Pressure at exit: 0.2272E+00 atm. (0.3339E+01 psia)
Temperature at exit: 1379.71 Kelvin.
Exit Velocity: 0.1337E+05 ft/sec.
Thrust at sea-level: +7.9815E+04 lbf.
Thrust at 10,000 ft: +8.6423E+04 lbf.
Thrust at 25,000 ft: +9.3124E+04 lbf.
Thrust at 50,000 ft: +9.8555E+04 lbf.
Thrust at 75,000 ft: +1.0024E+05 lbf.
Thrust at 100,000 ft: +1.0075E+05 lbf.
Thrust at 150,000 ft: +1.0095E+05 lbf.
Thrust in a vacuum: +1.0098E+05 lbf.
Normal Termination on 01-22-1988 at 17:57:09