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hlkyooizjgnqflfhtmrn.out
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*******************************************************************************
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
*******************************************************************************
problem rocket fr
p(psi) = 2500
o/f = 1
sup = 1.6469
reac
fuel = H2 t(K) = 297.000 wt% = 100.000
ox = O2 t(K) = 297.000 wt% = 100.000
outp trans
end
OPTIONS: TP=F HP=F SP=F TV=F UV=F SV=F DETN=F SHOCK=F REFL=F INCD=F
RKT=T FROZ=T EQL=F IONS=F SIUNIT=T DEBUGF=F SHKDBG=F DETDBG=F TRNSPT=T
TRACE= 0.00E+00 S/R= 0.000000E+00 H/R= 0.000000E+00 U/R= 0.000000E+00
Pc,BAR = 172.368261
Pc/P =
SUBSONIC AREA RATIOS =
SUPERSONIC AREA RATIOS = 1.6469
NFZ= 1 Mdot/Ac= 0.000000E+00 Ac/At= 0.000000E+00
REACTANT WT.FRAC (ENERGY/R),K TEMP,K DENSITY
EXPLODED FORMULA
F: H2 1.000000 -0.398787E+01 297.00 0.0000
H 2.00000
O: O2 1.000000 -0.406300E+01 297.00 0.0000
O 2.00000
SPECIES BEING CONSIDERED IN THIS SYSTEM
(CONDENSED PHASE MAY HAVE NAME LISTED SEVERAL TIMES)
LAST thermo.inp UPDATE: 9/09/04
g 6/97 *H g 4/02 HO2 tpis78 *H2
g 8/89 H2O g 6/99 H2O2 g 5/97 *O
g 4/02 *OH tpis89 *O2 g 8/01 O3
g11/99 H2O(cr) g 8/01 H2O(L) g 8/01 H2O(L)
SPECIES WITH TRANSPORT PROPERTIES
PURE SPECIES
H H2 H2O O
OH O2
BINARY INTERACTIONS
H H2
H O
H2 H2O
H2 O2
H2O O2
O O2
O/F = 1.000000
EFFECTIVE FUEL EFFECTIVE OXIDANT MIXTURE
ENTHALPY h(2)/R h(1)/R h0/R
(KG-MOL)(K)/KG -0.19782258E+01 -0.12697366E+00 -0.10525997E+01
KG-FORM.WT./KG bi(2) bi(1) b0i
*H 0.99212255E+00 0.00000000E+00 0.49606127E+00
*O 0.00000000E+00 0.62502344E-01 0.31251172E-01
POINT ITN T H O
1 10 1281.250 -6.570 -32.178
THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION
Pin = 2500.0 PSIA
CASE =
REACTANT WT FRACTION ENERGY TEMP
(SEE NOTE) KJ/KG-MOL K
FUEL H2 1.0000000 -33.157 297.000
OXIDANT O2 1.0000000 -33.782 297.000
O/F= 1.00000 %FUEL= 50.000000 R,EQ.RATIO= 7.936683 PHI,EQ.RATIO= 7.936683
CHAMBER THROAT EXIT
Pinf/P 1.0000 1.8638 7.2072
P, BAR 172.37 92.481 23.916
T, K 1281.25 1092.71 762.51
RHO, KG/CU M 6.5235 0 4.1040 0 1.5209 0
H, KJ/KG -8.7519 -1530.27 -4093.33
U, KJ/KG -2651.01 -3783.72 -5665.82
G, KJ/KG -45429.7 -40267.3 -31124.7
S, KJ/(KG)(K) 35.4505 35.4505 35.4505
M, (1/n) 4.032 4.032 4.032
Cp, KJ/(KG)(K) 8.1948 7.9477 7.6023
GAMMAs 1.3363 1.3504 1.3722
SON VEL,M/SEC 1879.0 1744.4 1469.0
MACH NUMBER 0.000 1.000 1.946
TRANSPORT PROPERTIES (GASES ONLY)
CONDUCTIVITY IN UNITS OF MILLIWATTS/(CM)(K)
VISC,MILLIPOISE 0.34491 0.30771 0.23563
WITH FROZEN REACTIONS
Cp, KJ/(KG)(K) 8.1948 7.9477 7.6023
CONDUCTIVITY 4.6091 4.0330 3.0443
PRANDTL NUMBER 0.6133 0.6064 0.5884
PERFORMANCE PARAMETERS
Ae/At 1.0000 1.6469
CSTAR, M/SEC 2407.7 2407.7
CF 0.7245 1.1871
Ivac, M/SEC 3036.2 3408.3
Isp, M/SEC 1744.4 2858.2
MOLE FRACTIONS
*H2 0.87400 H2O 0.12600
* THERMODYNAMIC PROPERTIES FITTED TO 20000.K
PRODUCTS WHICH WERE CONSIDERED BUT WHOSE MOLE FRACTIONS
WERE LESS THAN 5.000000E-06 FOR ALL ASSIGNED CONDITIONS
NOTE. WEIGHT FRACTION OF FUEL IN TOTAL FUELS AND OF OXIDANT IN TOTAL OXIDANTS