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throttle.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) = 105.2429
o/f = 1.2
sup = 1
reac
fuel = C3H8O,2propanol t(K) = 293.150 wt% = 100.000
ox = O2(L) t(K) = 90.170
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 = 7.256214
Pc/P =
SUBSONIC AREA RATIOS =
SUPERSONIC AREA RATIOS = 1.0000
NFZ= 1 Mdot/Ac= 0.000000E+00 Ac/At= 0.000000E+00
WARNING!! AMOUNT MISSING FOR REACTANT 2.
PROGRAM SETS WEIGHT PERCENT = 100. (REACT)
REACTANT WT.FRAC (ENERGY/R),K TEMP,K DENSITY
EXPLODED FORMULA
F: C3H8O,2propanol 1.000000 -0.328516E+05 293.15 0.0000
C 3.00000 H 8.00000 O 1.00000
O: O2(L) 1.000000 -0.156101E+04 90.17 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 7/97 *C tpis79 *CH g 4/02 CH2
g 4/02 CH3 g11/00 CH2OH g 7/00 CH3O
g 8/99 CH4 g 7/00 CH3OH srd 01 CH3OOH
tpis79 *CO g 9/99 *CO2 tpis91 COOH
tpis91 *C2 g 6/01 C2H g 1/91 C2H2,acetylene
g 5/01 C2H2,vinylidene g 4/02 CH2CO,ketene g 3/02 O(CH)2O
srd 01 HO(CO)2OH g 7/01 C2H3,vinyl g 6/96 CH3CO,acetyl
g 1/00 C2H4 g 8/88 C2H4O,ethylen-o g 8/88 CH3CHO,ethanal
g 6/00 CH3COOH srd 01 OHCH2COOH g 7/00 C2H5
g 7/00 C2H6 g 8/88 C2H5OH g 7/00 CH3OCH3
srd 01 CH3O2CH3 g 8/00 C2O tpis79 *C3
n 4/98 C3H3,1-propynl n 4/98 C3H3,2-propynl g 2/00 C3H4,allene
g 1/00 C3H4,propyne g 5/90 C3H4,cyclo- g 3/01 C3H5,allyl
g 2/00 C3H6,propylene g 1/00 C3H6,cyclo- g 6/01 C3H6O,propylox
g 6/97 C3H6O,acetone g 1/02 C3H6O,propanal g 7/01 C3H7,n-propyl
g 9/85 C3H7,i-propyl g 2/00 C3H8 g 2/00 C3H8O,1propanol
g 2/00 C3H8O,2propanol g 7/88 C3O2 g tpis *C4
g 7/01 C4H2,butadiyne g 8/00 C4H4,1,3-cyclo- n10/92 C4H6,butadiene
n10/93 C4H6,1butyne n10/93 C4H6,2butyne g 8/00 C4H6,cyclo-
n 4/88 C4H8,1-butene n 4/88 C4H8,cis2-buten n 4/88 C4H8,tr2-butene
n 4/88 C4H8,isobutene g 8/00 C4H8,cyclo- g10/00 (CH3COOH)2
n10/84 C4H9,n-butyl n10/84 C4H9,i-butyl g 1/93 C4H9,s-butyl
g 1/93 C4H9,t-butyl g12/00 C4H10,n-butane g 8/00 C4H10,isobutane
g 8/00 *C5 g 5/90 C5H6,1,3cyclo- g 1/93 C5H8,cyclo-
n 4/87 C5H10,1-pentene g 2/01 C5H10,cyclo- n10/84 C5H11,pentyl
g 1/93 C5H11,t-pentyl n10/85 C5H12,n-pentane n10/85 C5H12,i-pentane
n10/85 CH3C(CH3)2CH3 g 2/93 C6H2 g11/00 C6H5,phenyl
g 8/00 C6H5O,phenoxy g 8/00 C6H6 g 8/00 C6H5OH,phenol
g 1/93 C6H10,cyclo- n 4/87 C6H12,1-hexene g 6/90 C6H12,cyclo-
n10/83 C6H13,n-hexyl g 6/01 C6H14,n-hexane g 7/01 C7H7,benzyl
g 1/93 C7H8 g12/00 C7H8O,cresol-mx n 4/87 C7H14,1-heptene
n10/83 C7H15,n-heptyl n10/85 C7H16,n-heptane n10/85 C7H16,2-methylh
n 4/89 C8H8,styrene n10/86 C8H10,ethylbenz n 4/87 C8H16,1-octene
n10/83 C8H17,n-octyl n 4/85 C8H18,n-octane n 4/85 C8H18,isooctane
n10/83 C9H19,n-nonyl g 3/01 C10H8,naphthale n10/83 C10H21,n-decyl
g 8/00 C12H9,o-bipheny g 8/00 C12H10,biphenyl g 6/97 *H
g 1/01 HCO g 6/01 HCCO g 4/02 HO2
tpis78 *H2 g 5/01 HCHO,formaldehy g 6/01 HCOOH
g 8/89 H2O g 6/99 H2O2 g 6/01 (HCOOH)2
g 5/97 *O g 4/02 *OH tpis89 *O2
g 8/01 O3 n 4/83 C(gr) n 4/83 C(gr)
n 4/83 C(gr) g11/99 H2O(cr) g 8/01 H2O(L)
g 8/01 H2O(L)
SPECIES WITH TRANSPORT PROPERTIES
PURE SPECIES
C CH4 CH3OH CO
CO2 C2H2,acetylene
C2H4 C2H6 C2H5OH H
H2 H2O
O OH O2
BINARY INTERACTIONS
C O
CH4 O2
CO CO2
CO O2
CO2 H2
CO2 H2O
CO2 O2
H H2
H O
H2 H2O
H2 O2
H2O O2
O O2
O/F = 1.200000
EFFECTIVE FUEL EFFECTIVE OXIDANT MIXTURE
ENTHALPY h(2)/R h(1)/R h0/R
(KG-MOL)(K)/KG -0.54666124E+03 -0.48783267E+02 -0.27509143E+03
KG-FORM.WT./KG bi(2) bi(1) b0i
*C 0.49920942E-01 0.00000000E+00 0.22691337E-01
*H 0.13312251E+00 0.00000000E+00 0.60510233E-01
*O 0.16640314E-01 0.62502344E-01 0.41655967E-01
POINT ITN T C H O
1 21 2648.253 -13.476 -9.869 -19.265
THEORETICAL ROCKET PERFORMANCE ASSUMING FROZEN COMPOSITION
Pin = 105.2 PSIA
CASE =
REACTANT WT FRACTION ENERGY TEMP
(SEE NOTE) KJ/KG-MOL K
FUEL C3H8O,2propanol 1.0000000 -273145.105 293.150
OXIDANT O2(L) 1.0000000 -12979.000 90.170
O/F= 1.20000 %FUEL= 45.454545 R,EQ.RATIO= 1.815773 PHI,EQ.RATIO= 1.996763
CHAMBER THROAT EXIT
Pinf/P 1.0000 1.7970 1.7970
P, BAR 7.2562 4.0379 4.0379
T, K 2648.25 2365.51 2365.51
RHO, KG/CU M 6.1876-1 3.8548-1 3.8548-1
H, KJ/KG -2287.25 -2937.33 -2937.33
U, KJ/KG -3459.95 -3984.82 -3984.82
G, KJ/KG -37552.6 -34437.6 -34437.6
S, KJ/(KG)(K) 13.3165 13.3165 13.3165
M, (1/n) 18.776 18.776 18.776
Cp, KJ/(KG)(K) 2.3183 2.2788 2.2788
GAMMAs 1.2361 1.2412 1.2412
SON VEL,M/SEC 1204.0 1140.2 1140.2
MACH NUMBER 0.000 1.000 1.000
TRANSPORT PROPERTIES (GASES ONLY)
CONDUCTIVITY IN UNITS OF MILLIWATTS/(CM)(K)
VISC,MILLIPOISE 0.84226 0.77613 0.77613
WITH FROZEN REACTIONS
Cp, KJ/(KG)(K) 2.3183 2.2788 2.2788
CONDUCTIVITY 3.3298 2.9987 2.9987
PRANDTL NUMBER 0.5864 0.5898 0.5898
PERFORMANCE PARAMETERS
Ae/At 1.0000 1.0000
CSTAR, M/SEC 1650.9 1650.9
CF 0.6907 0.6907
Ivac, M/SEC 2058.9 2058.9
Isp, M/SEC 1140.2 1140.2
MOLE FRACTIONS
*CO 0.36569 *CO2 0.06037 *H 0.00898
*H2 0.26927 H2O 0.29302 *O 0.00005
*OH 0.00260 *O2 0.00002
* 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