Upper Stage Optimization

Upper Stage Optimization
NTO/MMH He & COPV Tanks	PRISM v1.1.7
by: Elly Kepler	May 05, 2018

PRIOR TO OPTIMIZATION
PRISM System: NTO/MMH He & COPV Tanks mass = 320.602 lbm type = bi-propellant ====================================== name value minimum maximum PHe 5000 4000 9000 Helium Tank Pressure (psia) Pc 150 150 500 Engine Chamber Pressure (psia) Figure of Merit = 320.602 = Total System Mass, lbm (sysMass) ====================================== ======================================

PRIOR TO OPTIMIZATION

PRISM System: NTO/MMH He & COPV Tanks 
                mass =      320.602 lbm
                type = bi-propellant
======================================
      name         value        minimum   maximum
       PHe         5000         4000         9000 Helium Tank Pressure  (psia)
        Pc          150          150          500 Engine Chamber Pressure  (psia)
 Figure of Merit = 320.602 = Total System Mass, lbm (sysMass)
======================================
======================================

AFTER OPTIMIZATION
PRISM System: NTO/MMH He & COPV Tanks mass = 314.819 lbm type = bi-propellant ====================================== name value minimum maximum PHe 8541.95 4000 9000 Helium Tank Pressure (psia) Pc 359.047 150 500 Engine Chamber Pressure (psia) Figure of Merit = 314.819 = Total System Mass, lbm (sysMass) ====================================== ======================================

AFTER OPTIMIZATION

PRISM System: NTO/MMH He & COPV Tanks 
                mass =      314.819 lbm
                type = bi-propellant
======================================
      name         value        minimum   maximum
       PHe      8541.95         4000         9000 Helium Tank Pressure  (psia)
        Pc      359.047          150          500 Engine Chamber Pressure  (psia)
 Figure of Merit = 314.819 = Total System Mass, lbm (sysMass)
======================================
======================================

System Sensitivity

Design Variables (nominal values)
Name	Value	Units	Description
MR	1.65		Engine Mixture Ratio
Pc	359.047	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	8541.95	psia	Helium Tank Pressure (psia)

Result Variables
Name	Value	Units	Description	Constrain	Limit
deltaV	901.2	ft/sec	Vacuum Delta Velocity (ft/sec)		=901.2
eps	133.609 * ----->		Axial Engine Area Ratio (eps varies to make Lengine = 15.6 in)		>10, <600
epsPY	31.9217 * ----->		PY Engine Area Ratio (epsPY varies to make LPYnoz = 1.5 in)		>1.2, <150
Isp	304.377	sec	Engine Specific Impulse (sec)		---
Itot	53516.8	lbf-sec	Total Impulse (lbf-sec)		---
Lengine	15.6	in	Axial Engine Length (in)		=15.6
LPYnoz	1.5	in	PY Engine Length (in)		=1.5
sysMass	314.819	lbm	Total System Mass (lbm)		---
WtPropAxial	175.824 * ----->	lbm	Total Usable Axial Propellant (lbm) (WtPropAxial varies to make deltaV = 901.2 ft/sec)		>10, <600

Mass Summary
System: NTO/MMH He & COPV Tanks	314.819	lbm	Total
Name	Mass	Units	Type
INERT
Axial Engine	5.405	lbm	inert
Axial Engine Fuel Line	0.363	lbm	inert
Axial Engine Ox Line	0.363	lbm	inert
Fuel Tank	10.884	lbm	inert
Helium Tank	9.804	lbm	inert
Oxidizer Tank	10.840	lbm	inert
PY Engines	6.886	lbm	inert
RCS Fuel Lines	3.498	lbm	inert
RCS Ox Lines	3.123	lbm	inert
Roll Engines	4.335	lbm	inert
Stage Misc.	50.000	lbm	inert
PRESSURANT
Helium Pressurant	2.504	lbm	pressurant
PROPELLANT
Monomethyl Hydrazine	80.298	lbm	propellant
Nitrogen Tetroxide	126.516	lbm	propellant

Design Variables (nominal values)
Name	Value	Units	Description
MR	1.65		Engine Mixture Ratio
Pc	359.047	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	8541.95	psia	Helium Tank Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
MR	1.65		Engine Mixture Ratio
Pc	359.047	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	8541.95	psia	Helium Tank Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
MR	1.65		Engine Mixture Ratio
Pc	359.047	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	8541.95	psia	Helium Tank Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
MR	1.65		Engine Mixture Ratio
Pc	359.047	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	8541.95	psia	Helium Tank Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
MR	1.65		Engine Mixture Ratio
pcentBell	80		Nozzle Percent Bell

Design Variables (nominal values)
Name	Value	Units	Description
MR	1.65		Engine Mixture Ratio
Pc	359.047	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	8541.95	psia	Helium Tank Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
MR	1.65		Engine Mixture Ratio
Pc	359.047	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	8541.95	psia	Helium Tank Pressure (psia)

Design Variable Summary

Design Variables (nominal values)
Name	Value	Units	Description
MR	1.65		Engine Mixture Ratio
Pc	359.047	psia	Engine Chamber Pressure (psia)
pcentBell	80		Nozzle Percent Bell
PHe	8541.95	psia	Helium Tank Pressure (psia)

Result Variables
Name	Value	Units	Description	Constrain	Limit
deltaV	901.2	ft/sec	Vacuum Delta Velocity (ft/sec)		=901.2
eps	133.609 * ----->		Axial Engine Area Ratio (eps varies to make Lengine = 15.6 in)		>10, <600
epsPY	31.9217 * ----->		PY Engine Area Ratio (epsPY varies to make LPYnoz = 1.5 in)		>1.2, <150
Isp	304.377	sec	Engine Specific Impulse (sec)		---
Itot	53516.8	lbf-sec	Total Impulse (lbf-sec)		---
Lengine	15.6	in	Axial Engine Length (in)		=15.6
LPYnoz	1.5	in	PY Engine Length (in)		=1.5
sysMass	314.819	lbm	Total System Mass (lbm)		---
WtPropAxial	175.824 * ----->	lbm	Total Usable Axial Propellant (lbm) (WtPropAxial varies to make deltaV = 901.2 ft/sec)		>10, <600

Bipropellant Engine: Axial Engine

mass = 5.405 lbm type = inert

Propellants : N2O4 / MMH

NASA CEA Code for ODE performance

Physical Weight Model

Injector Material is SS

Nozzle Material is Cb103

Bell Nozzle with Percent Bell = 80

==== INPUT ====
Name	Value	Units
Fvac	= 315	lbf
Pc	= 359.0	psia
eps	= 133.609
%Bell	= 80.00	%
mr	= 1.65
CR	= 2.5
xlnOverLcham	= 0.5
LoverDt	= 2
LchamMin	= 2.000	in
cxwInj	= 1
cxwValves	= 1
cxw	= 1.27
etaERE	= 0.94

==== OUTPUT ====
Name	Value	Units
Isp	= 304.377	sec
Cstar	= 5390.6	ft/sec
etaBL	= 0.974645
etaDiv	= 0.992212
etaKin	= 0.973074
etaNoz	= 0.941016
effIsp	= 0.884555
IspODE	= 344.102	sec
CstarODE	= 5734.7	ft/sec
Tc	= 5618.1	degR
PcFace	= 376.297	psia
Pexit	= 0.134175	psia
wdotTot	= 1.0349	lbm/sec
wdotOx	= 0.644372	lbm/sec
wdotFl	= 0.390529	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 12.3737	cuin/sec
volDotFl	= 12.3723	cuin/sec
DFlow	= 0.725	in
At	= 0.482927	sqin
Dt	= 0.784	in
Dcham	= 1.240	in
Dexit	= 9.064	in
Lcham	= 2.000	in
xlc	= 1.000	in
xln	= 1.000	in
Lnoz	= 12.360	in
Lengine	= 15.600	in
rhoInj	= 0.280	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 1.527	lbm
WtChamber	= 0.045	lbm
WtInj	= 0.507	lbm
WtAcoustic	= 0.471	lbm
WtValves(2)	= 2.037	lbm
WtMisc	= 0.102	lbm
F/W	= 58.277	lbf/lbm

Solenoid Valve: biprop valves

mass = 2.037 lbm type = inert

Based on Solenoid Valve Experience

Mass is for 2 valves total

==== INPUT ====
Name	Value	Units
cuInchPerSec	= 12.3737	cuin/sec
cxw	= 1.000

==== OUTPUT ====
Name	Value	Units
basemass	= 1.019	lbm

Liquid Line: Axial Engine Fuel Line

mass = 0.363 lbm type = inert

fluid : MMH

Structural Material : Ti

Allow Non-Standard wall thickness

==== INPUT ====
Name	Value	Units
wdot	= 0.390529	lbm/sec
velFPS	= 20	ft/sec
len_inches	= 24	in
Kfactors	= 10	vel heads
roughness	= 5e-06	in
thkInp	= 0	in
pLine	= 666.979	psia
sf	= 4
cxw	= 3.5
# Lines	= 1

==== OUTPUT ====
Name	Value	Units
dpLine	= 28.30	psig
ReNum	= 4.391018E+04
thkLine	= 0.030	in
rinsid	= 0.128	in
dinsid	= 0.256	in
doutside	= 0.316	in
volLine	= 1.23723	cuin
rho	= 0.16	lbm/cuin
sy	= 119000	psi
tming	= 0.030	in
fluid rho	= 0.0315646	lbm/cuin
fluid visc	= 53.04	1.0E5 * lb/ft-sec

Liquid Line: Axial Engine Ox Line

mass = 0.363 lbm type = inert

fluid : N2O4

Structural Material : Ti

Allow Non-Standard wall thickness

==== INPUT ====
Name	Value	Units
wdot	= 0.644372	lbm/sec
velFPS	= 20	ft/sec
len_inches	= 24	in
Kfactors	= 10	vel heads
roughness	= 5e-06	in
thkInp	= 0	in
pLine	= 666.979	psia
sf	= 4
cxw	= 3.5
# Lines	= 1

==== OUTPUT ====
Name	Value	Units
dpLine	= 44.90	psig
ReNum	= 1.442428E+05
thkLine	= 0.030	in
rinsid	= 0.128	in
dinsid	= 0.256	in
doutside	= 0.316	in
volLine	= 1.23737	cuin
rho	= 0.16	lbm/cuin
sy	= 119000	psi
tming	= 0.030	in
fluid rho	= 0.0520758	lbm/cuin
fluid visc	= 26.64	1.0E5 * lb/ft-sec

Cylindrical/Spherical/Elliptical Tank: Fuel Tank

mass = 10.884 lbm type = inert

Metal Tank Algorithm

Structural Material : grEpox

Bladder Thickness is input at 0.030 in

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 2622.6	cuin
vfreeTotal	= 2622.6	cuin
ell	= 1.767
rcyltd	= 1.445
ptank	= 666.979	psia
sf	= 1.5
cxw	= 1.5
ithcyl	= 1
kacqui	= 1	transverse collapsing Alum. bladder
inpex	= 1
expefi	= 0.98
tblad	= 0.030	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.098	lbm/cuin
tliner	= 0.030	in
rholiner	= 0.098	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 6.206	in
dinsid	= 12.412	in
OR	= 6.282	in
OD	= 12.564	in
OH	= 25.108	in
hinsid	= 24.960	in
SAinsid	= 1051.427	sqin
cyl	= 17.936	in
wacqui	= 3.049	lbm
vacqui	= 30.4917	cuin
dpacq	= 52.6791	psig
pullag	= 719.658	psia
vresid	= 52.452	cuin
vtank	= 2736.85	cuin
tming	= 0.008	in
thkcyl	= 0.016	in
thkend	= 0.014	in
thkBladOut	= 0.030	in
wliner	= 3.091	lbm
wtank(+liner)	= 4.207	lbm
rho	= 0.0637	lbm/cuin
sy	= 393000	psi
e	= 3.5e+07	psi
PmeopVoverW	= 167714	lbf-in/lbm
Pburst(est.)	= 1000.5	psia
PburstVoverW	= 251572	lbf-in/lbm

Cylindrical/Spherical/Elliptical Tank: Helium Tank

mass = 9.804 lbm type = inert

Composite Tank Algorithm

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 944.152	cuin
vfreeTotal	= 944.152	cuin
ell	= 1.764
rcyltd	= 1.142
ptank	= 8541.95	psia
sf	= 1.5
cxw	= 1
ithcyl	= 1
kacqui	= 0	no acq. device
inpex	= 0
expefi	= 0.99
tblad	= 0.030	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.28	lbm/cuin
tliner	= 0.065	in
rholiner	= 0.101	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 4.640	in
dinsid	= 9.280	in
OR	= 4.937	in
OD	= 9.873	in
OH	= 16.531	in
hinsid	= 15.859	in
SAinsid	= 505.929	sqin
cyl	= 10.598	in
wacqui	= 0.000	lbm
vacqui	= 0	cuin
dpacq	= 0	psig
pullag	= 8541.95	psia
vresid	= 9.93352	cuin
vtank	= 954.086	cuin
tming	= 0.008	in
thkcyl	= 0.202	in
thkend	= 0.241	in
thkBladOut	= 0.030	in
wliner	= 3.530	lbm
wtank(+liner)	= 9.804	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 831286	lbf-in/lbm
Pburst(est.)	= 12812.9	psia
PburstVoverW	= 1.24693e+06	lbf-in/lbm

Cylindrical/Spherical/Elliptical Tank: Oxidizer Tank

mass = 10.840 lbm type = inert

Composite Tank Algorithm

Bladder Thickness is input at 0.030 in

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 2504.6	cuin
vfreeTotal	= 2504.6	cuin
ell	= 1.767
rcyltd	= 1.445
ptank	= 666.979	psia
sf	= 1.5
cxw	= 1.5
ithcyl	= 1
kacqui	= 1	transverse collapsing Alum. bladder
inpex	= 1
expefi	= 0.98
tblad	= 0.030	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.098	lbm/cuin
tliner	= 0.030	in
rholiner	= 0.098	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 6.089	in
dinsid	= 12.177	in
OR	= 6.169	in
OD	= 12.337	in
OH	= 24.649	in
hinsid	= 24.487	in
SAinsid	= 1011.973	sqin
cyl	= 17.596	in
wacqui	= 2.957	lbm
vacqui	= 29.5676	cuin
dpacq	= 53.0025	psig
pullag	= 719.981	psia
vresid	= 50.0919	cuin
vtank	= 2584.26	cuin
tming	= 0.008	in
thkcyl	= 0.020	in
thkend	= 0.021	in
thkBladOut	= 0.030	in
wliner	= 3.117	lbm
wtank(+liner)	= 4.270	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 159003	lbf-in/lbm
Pburst(est.)	= 1000.5	psia
PburstVoverW	= 238504	lbf-in/lbm

Bipropellant Engine: PY Engines

mass = 6.886 lbm type = inert

Propellants : N2O4 / MMH

NASA CEA Code for ODE performance

Physical Weight Model

Injector Material is SS

Nozzle Material is Cb103

Bell Nozzle with Percent Bell = 80

Mass is for 6 engines total

==== INPUT ====
Name	Value	Units
Fvac	= 23	lbf
Pc	= 359.0	psia
eps	= 31.9217
%Bell	= 80.00	%
mr	= 1.2
CR	= 2.5
xlnOverLcham	= 0.5
LoverDt	= 2
LchamMin	= 1.500	in
cxwInj	= 1
cxwValves	= 1
cxw	= 1.5875
etaERE	= 0.9

==== OUTPUT ====
Name	Value	Units
Isp	= 271.441	sec
Cstar	= 5000.0	ft/sec
etaBL	= 0.976537
etaDiv	= 0.991441
etaKin	= 1
etaNoz	= 0.968179
effIsp	= 0.871361
IspODE	= 311.514	sec
CstarODE	= 5555.5	ft/sec
Tc	= 4802.9	degR
PcFace	= 376.297	psia
Pexit	= 0.807341	psia
wdotTot	= 0.0847328	lbm/sec
wdotOx	= 0.0462179	lbm/sec
wdotFl	= 0.0385149	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 0.887511	cuin/sec
volDotFl	= 1.22019	cuin/sec
DFlow	= 0.228	in
At	= 0.0366746	sqin
Dt	= 0.216	in
Dcham	= 0.342	in
Dexit	= 1.221	in
Lcham	= 1.500	in
xlc	= 0.750	in
xln	= 0.750	in
Lnoz	= 1.500	in
Lengine	= 3.342	in
rhoInj	= 0.280	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 0.027	lbm
WtChamber	= 0.010	lbm
WtInj	= 0.011	lbm
WtAcoustic	= 0.119	lbm
WtValves(2)	= 0.868	lbm
WtMisc	= 0.010	lbm
wt/Engine	= 1.148	lbm
F/W	= 20.040	lbf/lbm

Solenoid Valve: biprop valves

mass = 0.868 lbm type = inert

Based on Solenoid Valve Experience

Mass is for 2 valves total

==== INPUT ====
Name	Value	Units
cuInchPerSec	= 1.22019	cuin/sec
cxw	= 1.000

==== OUTPUT ====
Name	Value	Units
basemass	= 0.434	lbm

Liquid Line: RCS Fuel Lines

mass = 3.498 lbm type = inert

fluid : MMH

Structural Material : Ti

Allow Non-Standard wall thickness

Mass is for 10 lines total

==== INPUT ====
Name	Value	Units
wdot	= 0.0385149	lbm/sec
velFPS	= 20	ft/sec
len_inches	= 60	in
Kfactors	= 10	vel heads
roughness	= 5e-06	in
thkInp	= 0	in
pLine	= 666.979	psia
sf	= 4
cxw	= 3.5
# Lines	= 10

==== OUTPUT ====
Name	Value	Units
dpLine	= 74.59	psig
ReNum	= 1.378965E+04
thkLine	= 0.030	in
rinsid	= 0.040	in
dinsid	= 0.080	in
doutside	= 0.140	in
volLine	= 0.305048	cuin
rho	= 0.16	lbm/cuin
sy	= 119000	psi
tming	= 0.030	in
fluid rho	= 0.0315646	lbm/cuin
fluid visc	= 53.04	1.0E5 * lb/ft-sec
wt/Line	= 0.350	lbm

Liquid Line: RCS Ox Lines

mass = 3.123 lbm type = inert

fluid : N2O4

Structural Material : Ti

Allow Non-Standard wall thickness

Mass is for 10 lines total

==== INPUT ====
Name	Value	Units
wdot	= 0.0462179	lbm/sec
velFPS	= 20	ft/sec
len_inches	= 60	in
Kfactors	= 10	vel heads
roughness	= 5e-06	in
thkInp	= 0	in
pLine	= 666.979	psia
sf	= 4
cxw	= 3.5
# Lines	= 10

==== OUTPUT ====
Name	Value	Units
dpLine	= 115.17	psig
ReNum	= 3.863055E+04
thkLine	= 0.030	in
rinsid	= 0.034	in
dinsid	= 0.069	in
doutside	= 0.129	in
volLine	= 0.221878	cuin
rho	= 0.16	lbm/cuin
sy	= 119000	psi
tming	= 0.030	in
fluid rho	= 0.0520758	lbm/cuin
fluid visc	= 26.64	1.0E5 * lb/ft-sec
wt/Line	= 0.312	lbm

Bipropellant Engine: Roll Engines

mass = 4.335 lbm type = inert

Propellants : N2O4 / MMH

NASA CEA Code for ODE performance

Physical Weight Model

Injector Material is SS

Nozzle Material is Cb103

Bell Nozzle with Percent Bell = 80

Mass is for 4 engines total

==== INPUT ====
Name	Value	Units
Fvac	= 18	lbf
Pc	= 359.0	psia
eps	= 31.9217
%Bell	= 80.00	%
mr	= 1.2
CR	= 2.5
xlnOverLcham	= 0.5
LoverDt	= 2
LchamMin	= 1.500	in
cxwInj	= 1
cxwValves	= 1
cxw	= 1.5875
etaERE	= 0.9

==== OUTPUT ====
Name	Value	Units
Isp	= 271.275	sec
Cstar	= 5000.0	ft/sec
etaBL	= 0.97594
etaDiv	= 0.991441
etaKin	= 1
etaNoz	= 0.967587
effIsp	= 0.870828
IspODE	= 311.514	sec
CstarODE	= 5555.5	ft/sec
Tc	= 4802.9	degR
PcFace	= 376.297	psia
Pexit	= 0.807341	psia
wdotTot	= 0.0663532	lbm/sec
wdotOx	= 0.0361927	lbm/sec
wdotFl	= 0.0301606	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0521	lbm/cuin
volDotOx	= 0.694999	cuin/sec
volDotFl	= 0.955518	cuin/sec
DFlow	= 0.201	in
At	= 0.0287194	sqin
Dt	= 0.191	in
Dcham	= 0.302	in
Dexit	= 1.080	in
Lcham	= 1.500	in
xlc	= 0.750	in
xln	= 0.750	in
Lnoz	= 1.327	in
Lengine	= 3.130	in
rhoInj	= 0.280	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 0.022	lbm
WtChamber	= 0.009	lbm
WtInj	= 0.007	lbm
WtAcoustic	= 0.110	lbm
WtValves(2)	= 0.838	lbm
WtMisc	= 0.008	lbm
wt/Engine	= 1.084	lbm
F/W	= 16.607	lbf/lbm

Solenoid Valve: biprop valves

mass = 0.838 lbm type = inert

Based on Solenoid Valve Experience

Mass is for 2 valves total

==== INPUT ====
Name	Value	Units
cuInchPerSec	= 0.955518	cuin/sec
cxw	= 1.000

==== OUTPUT ====
Name	Value	Units
basemass	= 0.419	lbm

Miscellaneous Mass Items: Stage Misc.
mass = 50.000 lbm type = inert
All items are of type: inert

Helium Pressurant: Helium Pressurant

mass = 2.504 lbm type = pressurant

Polytropic Heat Transfer

==== INPUT ====
Name	Value	Units
VpropTnk	= 5127.2	cuin
PHeTnk	= 8541.95	psia
PpropNom	= 666.979	psia
PfinHeOvPnom	= 1.1
tAction	= 200	sec
TminR	= 510.0	degR
TmaxR	= 550.0	degR
tPolyCorr	= 240	sec
gamPolyCorr	= 1.66
gamLimPolyCorr	= 1

==== OUTPUT ====
Name	Value	Units
WHeTotal	= 2.504	lbm
WtHeResid	= 0.415	lbm
WHeExpended	= 2.089	lbm
volHeTotal	= 944.152	cuin
wdotHe	= 0.0104429	lbm/sec
compressInit	= 1.26645
PinitCold	= 7934.37	psia
densInitBot	= 4.5828	lbm/cuft
densFinalBot	= 0.760318	lbm/cuft
densFinalProp	= 0.703907	lbm/cuft
gammaPoly	= 1.19333
TfinalPropHe	= 341.5	degR
TfinalHeBot	= 346.8	degR
PfinalHeBot	= 733.7	psia

Incompressible Liquid: Monomethyl Hydrazine

mass = 80.298 lbm type = propellant

MMH Properties Calculated by Method of Corresponding States

==== INPUT ====
Name	Value	Units
T	= 530.0	degR
P	= 14.7	psia
Tref	= 530.0	degR
Tnbp	= 650.0	degR
Tcrit	= 1053.0	degR
Pref	= 14.7	psia
Pcrit	= 1195.0	psia
WtMol	= 46.07
RhoRef	= 0.0315646	lb/cuin
ViscRefFT	= 0.0005304	lb/ft-sec
CondRefFTHR	= 0.143294	BTU/ft-hr-R
CpRef	= 0.7	BTU/lbm degR
Burned Axial	= 66.349	lbm
Burned RCS	= 13.146	lbm
Residual	= 0.803	lbm

==== OUTPUT ====
Name	Value	Units
D	= 54.544	lbm/cuft
rho	= 0.0315646	lbm/cuin (0.873706 SG)
Cp	= 0.7	BTU/lbm degR
Visc	= 53.04	[1.0E5 * lb/ft-sec]
Cond	= 0.143294	BTU/ft-hr-R
SurfTen	= 0.0001932	lbf/in
phase	= LIQUID
Pvap	= 0.875502	psia
Vcuft	= 1.47218	cuft
Volume	= 2543.92	cuin

Incompressible Liquid: Nitrogen Tetroxide

mass = 126.516 lbm type = propellant

N2O4 Properties Calculated by Method of Corresponding States

==== INPUT ====
Name	Value	Units
T	= 530.0	degR
P	= 20.0	psia
Tref	= 530.0	degR
Tnbp	= 529.8	degR
Tcrit	= 776.5	degR
Pref	= 14.7	psia
Pcrit	= 1440.0	psia
WtMol	= 92.016
RhoRef	= 0.0520758	lb/cuin
ViscRefFT	= 0.0002664	lb/ft-sec
CondRefFTHR	= 0.0759456	BTU/ft-hr-R
CpRef	= 0.378	BTU/lbm degR
Burned Axial	= 109.475	lbm
Burned RCS	= 15.776	lbm
Residual	= 1.265	lbm

==== OUTPUT ====
Name	Value	Units
D	= 89.987	lbm/cuft
rho	= 0.0520758	lbm/cuin (1.44145 SG)
Cp	= 0.378	BTU/lbm degR
Visc	= 26.64	[1.0E5 * lb/ft-sec]
Cond	= 0.0759456	BTU/ft-hr-R
SurfTen	= 0.0001433	lbf/in
phase	= LIQUID
Pvap	= 14.7864	psia
Vcuft	= 1.40594	cuft
Volume	= 2429.46	cuin

(PRISM) PaRametrIc System Model
PRISM v1.1.7
contact: C. Taylor, cet@appliedpython.com