Lunar Lander

Lunar Lander
MON25/MMH solar ILN	PRISM v1.1.7
by: Moon Walker	May 05, 2018

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PcAxial	230	psia	Axial Engine Chamber Pressure (psia)
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

System Sensitivity

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PcAxial	230	psia	Axial Engine Chamber Pressure (psia)
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

Result Variables
Name	Value	Units	Description	Constrain	Limit
AreaRatio	94.6974		Descent Nozzle Area Ratio		---
dpBalOrificeACS	58.4333	psid	Balance Orifice Pressure Drop (psid)		---
dPinjector	115	psid	Injector Pressure Drop (psid)		---
dPvlvFuel	42.41	psid	Fuel Valve Pressure Drop (psid)		---
dPvlvMax	82.383	psid	Maximum Valve Pressure Drop (psid)		---
dPvlvOx	82.383	psid	Ox Valve Pressure Drop (psid)		---
engMass	12.0837	lbm	Total Engine Mass (lbm)		---
feedMass	1.57629	lbm	Valve/Line/Regulator Mass (lbm)		---
Isp	307.567	sec	Engine Specific Impulse (sec)		---
IspACS	280	sec	ACS Engine Specific Impulse (sec)		---
IspEff	307.567	sec	Effective Isp (with cant angle) (sec)		---
Lengine	13	in	Engine Length (in)		---
PcFace	241.05	psia	Engine Face Pressure (psia)		---
PengineIn	345	psia	Engine Inlet Pressure (psia)		---
PfinalHe	366.747	psia	Final Helium Pressure (psia)		---
Ptank	458.433	psia	Propellant Tank Pressure (psia)		---
sysMass	217.828	lbm	Total System Mass (lbm)		---
tankMass	22.9551	lbm	Total Tankage Mass (lbm)		---
VolRatioTanks	1.11002		Tank Volume Ratio (Ox/Fuel)		---

Mass Summary
System: MON25/MMH solar ILN	217.828	lbm	Total
Name	Mass	Units	Type
INERT
Axial Engine w/o Valves	6.084	lbm	inert
Axial Fuel valve	2.700	lbm	inert
Axial Ox valve	2.700	lbm	inert
COPV Helium Tank	6.041	lbm	inert
Fuel Line	0.643	lbm	inert
Fuel Tank	7.383	lbm	inert
Helium line	0.290	lbm	inert
Ox Line	0.643	lbm	inert
Ox Tank	9.531	lbm	inert
R-6D with valves	6.000	lbm	inert
PRESSURANT
Helium Pressurant	1.008	lbm	pressurant
PROPELLANT
MON-25	111.240	lbm	propellant
Monomethyl Hydrazine	63.566	lbm	propellant

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PcAxial	230	psia	Axial Engine Chamber Pressure (psia)
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PcAxial	230	psia	Axial Engine Chamber Pressure (psia)
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

Design Variable Summary

Design Variables (nominal values)
Name	Value	Units	Description
ItotACS	6518	lbf-sec	Total Impulse of ACS Engines (lbf-sec)
ItotDescent	46067	lbf-sec	Total Impulse of Descent Engines (lbf-sec)
LengLimit	13	in	Engine Length Limit (in)
mrAxial	1.75		Divert Engine Mixture Ratio
PcAxial	230	psia	Axial Engine Chamber Pressure (psia)
PmaxGas	4500	psia	Helium Max Bottle Pressure (psia)

Result Variables
Name	Value	Units	Description	Constrain	Limit
AreaRatio	94.6974		Descent Nozzle Area Ratio		---
dpBalOrificeACS	56.5406	psid	Balance Orifice Pressure Drop (psid)		---
dPinjector	115	psid	Injector Pressure Drop (psid)		---
dPvlvFuel	41.4356	psid	Fuel Valve Pressure Drop (psid)		---
dPvlvMax	80.4903	psid	Maximum Valve Pressure Drop (psid)		---
dPvlvOx	80.4903	psid	Ox Valve Pressure Drop (psid)		---
engMass	12.0837	lbm	Total Engine Mass (lbm)		---
feedMass	1.57629	lbm	Valve/Line/Regulator Mass (lbm)		---
Isp	307.567	sec	Engine Specific Impulse (sec)		---
IspACS	280	sec	ACS Engine Specific Impulse (sec)		---
IspEff	307.567	sec	Effective Isp (with cant angle) (sec)		---
Lengine	13	in	Engine Length (in)		---
PcFace	241.05	psia	Engine Face Pressure (psia)		---
PengineIn	345	psia	Engine Inlet Pressure (psia)		---
PfinalHe	365.232	psia	Final Helium Pressure (psia)		---
Ptank	456.541	psia	Propellant Tank Pressure (psia)		---
sysMass	217.807	lbm	Total System Mass (lbm)		---
tankMass	22.9368	lbm	Total Tankage Mass (lbm)		---
VolRatioTanks	1.11002		Tank Volume Ratio (Ox/Fuel)		---

Bipropellant Engine: Axial Engine w/o Valves

mass = 6.084 lbm type = inert

Propellants : MON25 / 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 3 engines total

==== INPUT ====
Name	Value	Units
Fvac	= 200	lbf
Pc	= 230.0	psia
eps	= 94.6974
%Bell	= 80.00	%
mr	= 1.75
CR	= 2.5
xlnOverLcham	= 0.9
LoverDt	= 2
LchamMin	= 1.250	in
cxwInj	= 1
cxwValves	= 0
cxw	= 1
etaERE	= 0.95

==== OUTPUT ====
Name	Value	Units
Isp	= 307.567	sec
Cstar	= 5471.4	ft/sec
etaBL	= 0.97415
etaDiv	= 0.992208
etaKin	= 0.975
etaNoz	= 0.942396
effIsp	= 0.895276
IspODE	= 343.545	sec
CstarODE	= 5759.4	ft/sec
Tc	= 5649.1	degR
PcFace	= 241.05	psia
Pexit	= 0.135298	psia
wdotTot	= 0.650264	lbm/sec
wdotOx	= 0.413804	lbm/sec
wdotFl	= 0.23646	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0501	lbm/cuin
volDotOx	= 8.25313	cuin/sec
volDotFl	= 7.49128	cuin/sec
DFlow	= 0.592	in
At	= 0.480793	sqin
Dt	= 0.782	in
Dcham	= 1.237	in
Dexit	= 7.614	in
Lcham	= 1.565	in
xlc	= 0.156	in
xln	= 1.408	in
Lnoz	= 10.198	in
Lengine	= 13.000	in
rhoInj	= 0.280	lbm/cuin
rhoNoz	= 0.310	lbm/cuin
thkCham	= 0.020	in
thkNoz	= 0.020	in
WtNoz	= 1.056	lbm
WtChamber	= 0.032	lbm
WtInj	= 0.504	lbm
WtAcoustic	= 0.368	lbm
WtValves(2)	= 0.000	lbm
WtMisc	= 0.068	lbm
wt/Engine	= 2.028	lbm
F/W	= 98.623	lbf/lbm

Liquid Valve: Axial Fuel valve (3)

mass = 2.700 lbm type = inert

fluid : MMH

Structural Material : Stainless Steel, Teflon

valve: MOOG Spacebus valve, Model 53-203

Mass is for 3 valves total

==== INPUT ====
Name	Value	Units
wdot	= 0.23646	lbm/sec
cxw	= 1
refWaterWdot	= 0.214	lbm/sec
refWaterDP	= 30	psid
# Valves	= 3

==== OUTPUT ====
Name	Value	Units
deltaP	= 42.41	psid
Kw	= 0.0390709	in-lb^.5/sec
velFluid	= 85.3927	ft/sec
CdA	= 0.00739903	sqin
fluid rho	= 0.0311875	lbm/cuin
fluid D	= 53.892	lbm/cuft
fluid visc	= 53.04	1.0E5 * lb/ft-sec
wt/Valve	= 0.900	lbm

Liquid Valve: Axial Ox valve (3)

mass = 2.700 lbm type = inert

fluid : MON25

Structural Material : Stainless Steel, Teflon

valve: MOOG Spacebus valve, Model 53-203

Mass is for 3 valves total

==== INPUT ====
Name	Value	Units
wdot	= 0.413804	lbm/sec
cxw	= 1
refWaterWdot	= 0.214	lbm/sec
refWaterDP	= 30	psid
# Valves	= 3

==== OUTPUT ====
Name	Value	Units
deltaP	= 82.38	psid
Kw	= 0.0390709	in-lb^.5/sec
velFluid	= 94.7877	ft/sec
CdA	= 0.00739903	sqin
fluid rho	= 0.0491685	lbm/cuin
fluid D	= 84.9632	lbm/cuft
fluid visc	= 26.7	1.0E5 * lb/ft-sec
wt/Valve	= 0.900	lbm

Cylindrical/Spherical/Elliptical Tank: COPV Helium Tank

mass = 6.023 lbm type = inert

Composite Tank Algorithm

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 681.375	cuin
vfreeTotal	= 681.375	cuin
ell	= 1.764
rcyltd	= 1.45
ptank	= 4500	psia
sf	= 2
cxw	= 1.25
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	= 0.1	lbm/cuin
tliner	= 0.040	in
rholiner	= 0.1	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 3.915	in
dinsid	= 7.829	in
OR	= 4.104	in
OD	= 8.208	in
OH	= 16.216	in
hinsid	= 15.790	in
SAinsid	= 419.384	sqin
cyl	= 11.352	in
wacqui	= 0.000	lbm
vacqui	= 0	cuin
dpacq	= 0	psig
pullag	= 4500	psia
vresid	= 7.55997	cuin
vtank	= 688.935	cuin
tming	= 0.050	in
thkcyl	= 0.119	in
thkend	= 0.143	in
thkBladOut	= 0.030	in
wliner	= 1.765	lbm
wtank(+liner)	= 4.818	lbm
rho	= 0.0637	lbm/cuin
PmeopVoverW	= 514721	lbf-in/lbm
Pburst(est.)	= 9000.0	psia
PburstVoverW	= 1.02944e+06	lbf-in/lbm

Liquid Line: Fuel Line

mass = 0.643 lbm type = inert

fluid : MMH

Structural Material : Ti

==== INPUT ====
Name	Value	Units
wdot	= 0.748355	lbm/sec
OD	= 0.500	in
thkWall	= 0.045	in
len_inches	= 50	in
Kfactors	= 5	vel heads
roughness	= 5e-06	in
pLine	= 456.541	psia
cxw	= 1.25
# Lines	= 1

==== OUTPUT ====
Name	Value	Units
dpLine	= 10.05	psid
dPperVelHead	= 1.33	psid
velFPS	= 15.1457	ft/sec
ReNum	= 5.257893E+04
rinsid	= 0.205	in
dinsid	= 0.410	in
volLine	= 6.60127	cuin
rho	= 0.16	lbm/cuin
sy	= 119000	psi

sf	= 57.2171
tming	= 0.030	in
fluid rho	= 0.0311875	lbm/cuin
fluid visc	= 53.04	1.0E5 * lb/ft-sec

Cylindrical/Spherical/Elliptical Tank: Fuel Tank

mass = 7.383 lbm type = inert

Metal Tank Algorithm

Structural Material : Ti

Bladder Thickness is input at 0.030 in

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 2101.21	cuin
vfreeTotal	= 2101.21	cuin
ell	= 1
rcyltd	= 0
ptank	= 456.541	psia
sf	= 1.5
cxw	= 1.5
ithcyl	= 1
kacqui	= 7	elastomeric transverse bladder (dP=0)
inpex	= 1
expefi	= 0.98
tblad	= 0.030	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.04	lbm/cuin
tliner	= 0.000	in
rholiner	= 0.04	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 8.028	in
dinsid	= 16.055	in
OR	= 8.088	in
OD	= 16.175	in
OH	= 16.175	in
hinsid	= 16.055	in
SAinsid	= 809.795	sqin
cyl	= 0.000	in
wacqui	= 0.946	lbm
vacqui	= 23.6509	cuin
dpacq	= 0	psig
pullag	= 504.01	psia
vresid	= 42.0242	cuin
vtank	= 2166.88	cuin
tming	= 0.030	in
thkcyl	= 0.030	in (use tming)
thkend	= 0.030	in (use tming)
thkBladOut	= 0.030	in
wtank	= 3.976	lbm
rho	= 0.16	lbm/cuin
sy	= 119000	psi
e	= 1.5e+07	psi
PmeopVoverW	= 133989	lbf-in/lbm
Pburst(est.)	= 444.7	psia
PburstVoverW	= 130519	lbf-in/lbm

Gas Line: Helium line

mass = 0.290 lbm type = inert

In: HE T= 320.2 P= 479.0 D=0.5433 E=241.02 H=404.28 S=4.315 Supercrit

Out:HE T= 320.4 P= 456.5 D=0.5182 E=241.14 H=404.28 S=4.339 Supercrit

fluid : HE

Structural Material : Ti

Allow Non-Standard wall thickness

Using Poutlet to design line

Line Diameter is an Input (vel is output)

==== INPUT ====
Name	Value	Units
wdot	= 0.0151911	lbm/sec
DiamInp	= 0.250	in
thkWallInp	= 0.045	in
len_inches	= 50	in
Kfactors	= 5	vel heads
roughness	= 5e-06	in
PgasOutlet	= 456.5	psia
sf	= 4
cxw	= 1.25
# Lines	= 1

==== OUTPUT ====
Name	Value	Units
PgasInlet	= 479.0	psia
velFPS	= 209.847	ft/sec
velHead	= 2.582	psi
dpLine	= 22.48	psig
dp due to Line	= 10.48	psig
dp due to Ks	= 12.00	psig
dp/Pinlet	= 0.0469366
ReNum	= 1.551340E+05
fricfact	= 0.0139809
thkLine	= 0.045	in
rinsid	= 0.080	in
dinsid	= 0.160	in
volLine	= 1.00531	cuin
rho	= 0.16	lbm/cuin
sy	= 119000	psi
tming	= 0.035	in
fluid dens	= 0.543328	lbm/cuft
fluid visc	= 9.58486e-06	lb/ft-sec
fluid sonicV	= 2640.01	ft/sec
fluid Mach	= 0.0794873

Liquid Line: Ox Line

mass = 0.643 lbm type = inert

fluid : MON25

Structural Material : Ti

==== INPUT ====
Name	Value	Units
wdot	= 1.30962	lbm/sec
OD	= 0.500	in
thkWall	= 0.045	in
len_inches	= 50	in
Kfactors	= 5	vel heads
roughness	= 5e-06	in
pLine	= 456.541	psia
cxw	= 1.25
# Lines	= 1

==== OUTPUT ====
Name	Value	Units
dpLine	= 18.04	psid
dPperVelHead	= 2.59	psid
velFPS	= 16.812	ft/sec
ReNum	= 1.827856E+05
rinsid	= 0.205	in
dinsid	= 0.410	in
volLine	= 6.60127	cuin
rho	= 0.16	lbm/cuin
sy	= 119000	psi

sf	= 57.2171
tming	= 0.030	in
fluid rho	= 0.0491685	lbm/cuin
fluid visc	= 26.7	1.0E5 * lb/ft-sec

Cylindrical/Spherical/Elliptical Tank: Ox Tank

mass = 9.531 lbm type = inert

Metal Tank Algorithm

Structural Material : Ti

kalmod = 0

==== INPUT ====
Name	Value	Units
vfree	= 2332.39	cuin
vfreeTotal	= 2332.39	cuin
ell	= 1
rcyltd	= 0
ptank	= 456.541	psia
sf	= 1.5
cxw	= 1.5
ithcyl	= 1
kacqui	= 6	capillary device
inpex	= 1
expefi	= 0.98
tblad	= 0.030	in
tbond	= 0.030	in
ttrspc	= 0.010	in
rhobnd	= 0.04	lbm/cuin
rhoacq	= 0.16	lbm/cuin
tliner	= 0.000	in
rholiner	= 0.04	lbm/cuin

==== OUTPUT ====
Name	Value	Units
rinsid	= 8.297	in
dinsid	= 16.593	in
OR	= 8.357	in
OD	= 16.713	in
OH	= 16.713	in
hinsid	= 16.593	in
SAinsid	= 865.003	sqin
cyl	= 0.000	in
wacqui	= 2.108	lbm
vacqui	= 13.1753	cuin
dpacq	= 0	psig
pullag	= 456.541	psia
vresid	= 46.6478	cuin
vtank	= 2392.21	cuin
tming	= 0.030	in
thkcyl	= 0.030	in (use tming)
thkend	= 0.030	in (use tming)
thkBladOut	= 0.030	in
wtank	= 4.246	lbm
rho	= 0.16	lbm/cuin
sy	= 119000	psi
e	= 1.5e+07	psi
PmeopVoverW	= 114594	lbf-in/lbm
Pburst(est.)	= 430.3	psia
PburstVoverW	= 108006	lbf-in/lbm

Bipropellant Engine: R-6D with valves (6)

mass = 6.000 lbm type = inert

Propellants : MON25 / MMH

NASA CEA Code for ODE performance

Actual Hardware Weight

Bell Nozzle with Percent Bell = 80

Mass is for 6 engines total

==== INPUT ====
Name	Value	Units
Pc	= 92.0	psia
Dt	= 0.207	in
eps	= 100
%Bell	= 80.00	%
mr	= 1.75
CR	= 2.5
Lprime	= 3.000	in
xlc/xln	= 1
etaERE	= 0.97

==== OUTPUT ====
Name	Value	Units
Fvac	= 5.00198	lbf
Isp	= 280	sec
Cstar	= 5554.7	ft/sec
etaNoz	= 0.839711
effIsp	= 0.81452
IspODE	= 343.761	sec
CstarODE	= 5726.5	ft/sec
Tc	= 5512.2	degR
wdotTot	= 0.0178642	lbm/sec
wdotOx	= 0.0113681	lbm/sec
wdotFl	= 0.00649608	lbm/sec
rhoFl	= 0.0316	lbm/cuin
rhoOx	= 0.0501	lbm/cuin
volDotOx	= 0.226732	cuin/sec
volDotFl	= 0.205802	cuin/sec
At	= 0.0335236	sqin
Dcham	= 0.327	in
Dexit	= 2.066	in
xlc	= 1.500	in
xln	= 1.500	in
Lcham	= 3.000	in
Lnoz	= 2.776	in
Lengine	= 6.102	in
wt/Engine	= 1.000	lbm
F/W	= 5.002	lbf/lbm

Helium Pressurant: Helium Pressurant

mass = 1.005 lbm type = pressurant

Integrated Heat Transfer

==== INPUT ====
Name	Value	Units
VpropTnk	= 4433.6	cuin
PGasTnkMEOP	= 4500	psia
PpropNom	= 456.541	psia
PfinGasOvPnom	= 0.8
tAction	= 318	sec
TminR	= 456.0	degR
TmaxR	= 582.0	degR

==== OUTPUT ====
Name	Value	Units
WGasTotal	= 1.005	lbm
WtGasResid	= 0.164	lbm
WtHeLLACS	= 0.100	lbm
WGasNon-Resid	= 0.840	lbm
Vbottle	= 681.375	cuin
wdotGas	= 0.00264261	lbm/sec
compressInit	= 1.13565
PbottleCold	= 3536.96	psia
densInitBot	= 2.54803	lbm/cuft
densFinalBot	= 0.416857	lbm/cuft
densFinalProp	= 0.383685	lbm/cuft
gammaIsen	= 1.64101
gamPolyBottle	= 1.1844
gamPolyTank	= 1.02035
fracIsenBottle	= 0.28768
fracIsenTank	= 0.0317405
TfinalPropGas	= 435.8	degR
TfinalGasBot	= 320.2	degR
PfinalGasBot	= 365.2	psia

Incompressible Liquid: MON-25

mass = 111.240 lbm type = propellant

MON25 Properties Calculated by Method of Corresponding States

==== INPUT ====
Name	Value	Units
T	= 550.0	degR
P	= 100.0	psia
Tref	= 530.0	degR
Tnbp	= 475.6	degR
Tcrit	= 747.0	degR
Pref	= 14.7	psia
Pcrit	= 2100.0	psia
WtMol	= 60.7
RhoRef	= 0.050139	lb/cuin
ViscRefFT	= 0.000267	lb/ft-sec
CondRefFTHR	= 0.0759456	BTU/ft-hr-R
CpRef	= 0.336	BTU/lbm degR
Burned Axial	= 95.314	lbm
Burned ACS	= 14.814	lbm
Margin	= 0.000	lbm
Leakage	= 0.000	lbm
Residual	= 1.112	lbm

==== OUTPUT ====
Name	Value	Units
D	= 84.963	lbm/cuft
rho	= 0.0491685	lbm/cuin (1.36098 SG)
Cp	= 0.336	BTU/lbm degR
Visc	= 26.7	[1.0E5 * lb/ft-sec]
Cond	= 0.0759456	BTU/ft-hr-R
SurfTen	= 0.000131139	lbf/in
phase	= LIQUID
Pvap	= 99.2407	psia
Vcuft	= 1.30927	cuft
Volume	= 2262.42	cuin

Incompressible Liquid: Monomethyl Hydrazine

mass = 63.566 lbm type = propellant

MMH Properties Calculated by Method of Corresponding States

==== INPUT ====
Name	Value	Units
T	= 550.0	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	= 54.465	lbm
Burned ACS	= 8.465	lbm
Margin	= 0.000	lbm
Leakage	= 0.000	lbm
Residual	= 0.636	lbm

==== OUTPUT ====
Name	Value	Units
D	= 53.892	lbm/cuft
rho	= 0.0311875	lbm/cuin (0.863267 SG)
Cp	= 0.7	BTU/lbm degR
Visc	= 53.04	[1.0E5 * lb/ft-sec]
Cond	= 0.143294	BTU/ft-hr-R
SurfTen	= 0.000184989	lbf/in
phase	= LIQUID
Pvap	= 1.54936	psia
Vcuft	= 1.1795	cuft
Volume	= 2038.17	cuin

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