### Install RocketProps from source Source: https://rocketprops.readthedocs.io/en/latest/_sources/quickstart.rst.txt Installation commands for local source code directories. ```bash cd full/path/to/rocketprops pip install -e . OR on Linux sudo pip install -e . OR perhaps pip install --user -e . ``` -------------------------------- ### Install RocketProps via pip Source: https://rocketprops.readthedocs.io/en/latest/_sources/quickstart.rst.txt Standard installation commands for RocketProps. ```bash pip install rocketprops OR on Linux sudo pip install rocketprops OR perhaps pip install --user rocketprops ``` -------------------------------- ### Verify RocketProps installation Source: https://rocketprops.readthedocs.io/en/latest/_sources/quickstart.rst.txt Terminal command to test the installation by printing properties for N2O4. ```bash python -c "from rocketprops.rocket_prop import get_prop; p=get_prop('N2O4'); p.summ_print()" ``` -------------------------------- ### RocketProps output example Source: https://rocketprops.readthedocs.io/en/latest/quickstart.html Expected output format when running the verification command. ```text ====== RocketProps State Point of Liquid N2O4 ===== Name = N2O4 (MON-3, MON3) T = 527.67 degR P = 14.6959 psia Pvap = 13.7843 psia Pc = 1441.3 psia Tc = 776.47 degR SGliq = 1.44144 g/cc SGvap = 0.00367439 g/cc visc = 0.00420093 poise cond = 0.0766961 BTU/hr/ft/delF Tnbp = 530.07 degR Tfreeze = 471.42 degR Cp = 0.374677 BTU/lbm/delF MolWt = 92.011 g/gmole Hvap = 178.2 BTU/lbm surf = 0.000149673 lbf/in ``` -------------------------------- ### Define Mixture Ratios Source: https://rocketprops.readthedocs.io/en/latest/_sources/mixtures.rst.txt Examples of weight-based mixture definitions for non-default propellants. ```python M20 = (20% MMH + 80%N2H4) MON3 = (3% NO + 97% N2O4) FLOX70 = (70% LF2 + 30% LOX) ``` -------------------------------- ### Define Propellant Mixture Definitions Source: https://rocketprops.readthedocs.io/en/latest/mixtures.html Examples of weight-percentage based propellant mixture definitions. ```text M20 = (20% MMH + 80%N2H4) MON3 = (3% NO + 97% N2O4) FLOX70 = (70% LF2 + 30% LOX) ``` -------------------------------- ### Compare Mixed Oxides of Nitrogen via Plots Source: https://rocketprops.readthedocs.io/en/latest/_sources/mixtures.rst.txt Generate comparative plots for various MON mixtures and N2O4. ```python from rocketprops.plot_multi_props import make_plots make_plots( ['MON30', 'MON25', 'MON10', 'MON3', 'N2O4'], abs_T=True, Tmin=480, Tmax=600, save_figures=False) ``` -------------------------------- ### Compare FLOX Mixtures via Plots Source: https://rocketprops.readthedocs.io/en/latest/_sources/mixtures.rst.txt Generate comparative plots for LF2, FLOX70, and LOX propellants. ```python from rocketprops.plot_multi_props import make_plots make_plots( ['LF2', 'FLOX70', 'LOX'], abs_T=1, Tmin=130, Tmax=170, save_figures=True) ``` -------------------------------- ### Create Density Table Source: https://rocketprops.readthedocs.io/en/latest/_sources/quickstart.rst.txt Python script to iterate through a list of propellants and print a formatted density table. ```python from rocketprops.rocket_prop import get_prop from rocketprops.unit_conv_data import get_value propL = ['A50','Methane','CLF5','Ethane','Ethanol','F2','IRFNA','LOX','M20', 'Methanol','MMH','MHF3','MON10','MON25','MON30','N2H4','N2O','N2O4', 'NH3','PH2','Propane','UDMH','RP1','Water','H2O2', 'Peroxide_70','Peroxide_85','Peroxide_95','Peroxide_100'] dataD = {} # key=pname, value=(SGref, data string) print( ' Propellant density Tref Tnbp SGnbp') for pname in propL: pobj = get_prop( pname ) Tref_C = get_value( pobj.T, 'degR', 'degC') Tnbp_C = get_value( pobj.Tnbp, 'degR', 'degC') SG_nbp = pobj.SGLiqAtTdegR( pobj.Tnbp ) dataD[ pname ] = (pobj.SG, '%5.2f SG %8.1f b0C'%( pobj.SG, Tref_C ) +\ '%8.1f b0C %5.2f SG'%( Tnbp_C, SG_nbp )) keyL = sorted( dataD, key=dataD.get, reverse=True ) for pname in keyL: print( '%12s'%pname, dataD[pname][1]) ``` -------------------------------- ### Compare Propellant Properties via Plots Source: https://rocketprops.readthedocs.io/en/latest/mixtures.html Generate comparative plots for various propellant mixtures and pure substances. ```python from rocketprops.plot_multi_props import make_plots make_plots( ['MMH', 'M20', 'N2H4'], abs_T=True, Tmin=480, Tmax=600) ``` ```python from rocketprops.plot_multi_props import make_plots make_plots( ['UDMH','A25', 'A50', 'N2H4'], abs_T=1, Tmin=130, Tmax=170, save_figures=True) ``` ```python from rocketprops.plot_multi_props import make_plots make_plots( ['MON30', 'MON25', 'MON10', 'MON3', 'N2O4'], abs_T=True, Tmin=480, Tmax=600, save_figures=False) ``` ```python from rocketprops.plot_multi_props import make_plots make_plots( ['LF2', 'FLOX70', 'LOX'], abs_T=1, Tmin=130, Tmax=170, save_figures=True) ``` -------------------------------- ### Compare Aerozine Mixtures via Plots Source: https://rocketprops.readthedocs.io/en/latest/_sources/mixtures.rst.txt Generate comparative plots for UDMH, A25, A50, and N2H4 propellants. ```python from rocketprops.plot_multi_props import make_plots make_plots( ['UDMH','A25', 'A50', 'N2H4'], abs_T=1, Tmin=130, Tmax=170, save_figures=True) ``` -------------------------------- ### Retrieve and plot propellant properties Source: https://rocketprops.readthedocs.io/en/latest/_sources/quickstart.rst.txt Initializes a propellant object for a specific chemical and generates saturation property plots. ```python from rocketprops.rocket_prop import get_prop p = get_prop('c3h8') p.plot_sat_props(save_figures=True) ``` -------------------------------- ### Compare MMH/N2H4 Mixtures via Plots Source: https://rocketprops.readthedocs.io/en/latest/_sources/mixtures.rst.txt Generate comparative plots for MMH, M20, and N2H4 propellants. ```python from rocketprops.plot_multi_props import make_plots make_plots( ['MMH', 'M20', 'N2H4'], abs_T=True, Tmin=480, Tmax=600) ``` -------------------------------- ### Calculate Propellant Line Parameters Source: https://rocketprops.readthedocs.io/en/latest/_sources/examples.rst.txt Calculates propellant line diameter and pressure drop using rocketprops.line_supt. ```python from rocketprops.line_supt import calc_line_id_dp, calc_line_vel_dp from rocketprops.rocket_prop import get_prop pObj = get_prop('hydrazine') ID, deltaP = calc_line_id_dp( pObj, TdegR=530.0, Ppsia=240.0, wdotPPS=0.5, velFPS=13, roughness=5.0E-6, Kfactors=5.0, len_inches=50.0) print( 'Inside Diam=%g inches, Pressure Drop =%g psid'%(ID, deltaP) ) vel, dp = calc_line_vel_dp( pObj, TdegR=530.0, Ppsia=240.0, wdotPPS=0.5, IDinches=ID, roughness=5.0E-6, Kfactors=5.0, len_inches=50.0) print( 'Velocity = %g ft/sec, Pressure Drop =%g psid'%(vel, deltaP) ) ``` -------------------------------- ### Calculate Valve Pressure Drop Source: https://rocketprops.readthedocs.io/en/latest/_sources/examples.rst.txt Compares valve pressure drops using imperial (Cv) and metric (Kv) flow coefficients via rocketprops.valve_supt. ```python from rocketprops.rocket_prop import get_prop from rocketprops.valve_supt import cv_valve_dp, kv_valve_dp """ Calculate the pressure drop across an MMH valve with given mass flow rate """ pObj = get_prop( 'MMH' ) # Imperial valve flow coefficient, Cv dp = cv_valve_dp( pObj, Cv=1.0, wdotPPS=0.5, TdegR=530.0, Ppsia=1000.0) print('Cv = 1.0 deltaP = %g psid'%dp) # Metric valve flow coefficient, Kv Kv = 1.0 / 1.1560992283526375 # Conversion factor for Cv to Kv dp = kv_valve_dp( pObj, Kv=Kv, wdotPPS=0.5, TdegR=530.0, Ppsia=1000.0) print('Kv = 1.0/convFact deltaP = %g psid'%dp) ``` -------------------------------- ### Sastri-Rao Surface Tension Scaling Constants Source: https://rocketprops.readthedocs.io/en/latest/models.html Provides the derived curve-fit values for the exponent n used in the Sastri-Rao surface tension scaling equation for specific propellants. ```text n N2H4 = 1.322137 N2O4 = 0.960017 A50 = 1.000717 MHF3 = 0.859508 MMH = 0.846186 UDMH = 1.018771 ``` -------------------------------- ### rocketprops.rocket_prop.build_mixture Source: https://rocketprops.readthedocs.io/en/latest/functions.html Builds a propellant mixture object. ```APIDOC ## rocketprops.rocket_prop.build_mixture(prop_name='') ### Description Build a mixture of MMH + N2H4 (e.g. M20), N2O4 + NO (e.g. MON25) or LOX + F2 (e.g. FLOX70). ### Parameters - **prop_name** (string) - Optional - Name of the mixture to build. ### Returns - **Propellant** (object) - Propellant object of the mixture. ``` -------------------------------- ### Retrieve and Print Mixture Properties Source: https://rocketprops.readthedocs.io/en/latest/_sources/mixtures.rst.txt Retrieve a propellant mixture object by name and display its state point summary. ```python from rocketprops.rocket_prop import get_prop Pm20 = get_prop( 'M20' ) Pm20.summ_print() ``` -------------------------------- ### Wagner Equation Constants for Propellants Source: https://rocketprops.readthedocs.io/en/latest/models.html Fitted constants a, b, c, and d for the Wagner vapor pressure equation across various propellants. ```text a b c d Methane -6.02242, 1.26652, -0.5707, -1.366 Methanol -8.63571, 1.17982, -2.4790, -1.0240 Ethane -6.47500, 1.41071, -1.1440, -1.8590 Ethanol -8.68587, 1.17831, -4.8762, 1.5880 Propane -6.76368, 1.55481, -1.5872, -2.024 NH3 -7.28322, 1.5716, -1.85672, -2.39312 PH2 -4.902616, 1.06500, 0.737305, 0.053125 N2H4 -6.7779260205203515, 0.031241419877672347, -1.75576214157275, -0.6791935603862034 N2O4 -8.437950623751371, -3.7198359775967993, 3.2683044393949223, 12.45086649764585 A50 -7.641659365830601, 3.2061563372352757, -2.9346526057929907, 2.9995620039010578 MHF3 -4.430400554283357, -4.289202857522381, 0.4548211727181293, 1.9771250142385894 MMH -6.700466713713631, -0.09747624183487236, -0.7874544884949485, -6.37220831093827 UDMH -7.335910621921567, -0.07120599848815566, 1.0118500681251754, -9.504291228049002 MON10 -8.859867572622312, -0.23569425311772815, -1.21511310516509, -2.7924844994111235 MON25 -8.626779322479342, -0.2877745218667564, -1.2609528745852392, -3.1994074964463137 MON30 -8.394164877030429, -0.3811184987718641, -1.1304799873211373, -3.5220091386630217 IRFNA -6.198317212258754, -3.187645737139488, 4.993054204407724, -14.807512940520226 ``` -------------------------------- ### Display Mixture State Point Output Source: https://rocketprops.readthedocs.io/en/latest/_sources/mixtures.rst.txt The console output generated by the summ_print() method for an M20 mixture. ```text ====== RocketProps State Point of Liquid M20 ===== Name = M20 (20.0% MMH + 80.0% N2H4) T = 527.67 degR P = 14.6959 psia Pvap = 0.300351 psia Pc = 1931.86 psia Tc = 1150.96 degR SGliq = 0.980694 g/cc SGvap = 3.16643e-05 g/cc visc = 0.0100714 poise cond = 0.270383 BTU/hr/ft/delF Tnbp = 686.45 degR Tfreeze = 483.55 degR Cp = 0.733093 BTU/lbm/delF MolWt = 34.1231 g/gmole Hvap = 533.465 BTU/lbm surf = 0.000359821 lbf/in ``` -------------------------------- ### Visc_compressed Source: https://rocketprops.readthedocs.io/en/latest/functions.html Calculates the viscosity of a liquid adjusted for high pressure. ```APIDOC ## Visc_compressed(TdegR, Ppsia) ### Description Adjusts viscosity of a liquid for high pressure using an empirical formula developed by Lucas. ### Parameters - **TdegR** (float) - Required - Temperature in degR - **Ppsia** (float) - Required - Pressure in psia ### Returns - **viscosity** (float) - Viscosity at (TdegR, Ppsia) in poise. ``` -------------------------------- ### Daubert Equation Constants for MON Mixtures Source: https://rocketprops.readthedocs.io/en/latest/models.html Curve-fitted parameters A, B, C, and D for MON10, MON25, and MON30 propellants used in the Daubert density equation. ```text A B C D MON10 184.6090958200138, 97.08205370646357, 852.8788442633142, -0.30396612785737676 MON25 148.1481569994554, 79.40853919233791, 871.4077962994412, -0.3164174025669882 MON30 179.63314607505583, 98.3583884965557, 869.460001600849, -0.29906872709771604 ``` -------------------------------- ### rocketprops.valve_supt.calib_valve_dp Source: https://rocketprops.readthedocs.io/en/latest/functions.html Calculates the pressure drop for a valve that has been calibrated using a water flow test. ```APIDOC ## rocketprops.valve_supt.calib_valve_dp(pObj, wdotPPS=0.5, TdegR=530.0, Ppsia=1000.0, refWaterWdot=0.214, refWaterDP=30.0) ### Description Calculate valve pressure drop for a valve that has been calibrated with a water flow test. ### Parameters - **pObj** (Propellant) - Required - Propellant object - **wdotPPS** (float) - Optional - Propellant mass flow rate in line, lbm/sec - **TdegR** (float) - Optional - Propellant temperature, degR - **Ppsia** (float) - Optional - Propellant inlet pressure to valve, psia - **refWaterWdot** (float) - Optional - Reference water flow rate, lbm/sec - **refWaterDP** (float) - Optional - Reference water pressure drop, psid ### Returns - **float** - Propellant pressure drop, psid ``` -------------------------------- ### Calculate Propellant Tank Volume Source: https://rocketprops.readthedocs.io/en/latest/_sources/examples.rst.txt Calculates the required volume of a propellant tank using rocketprops.tank_supt.calc_tank_volume. ```python from rocketprops.tank_supt import calc_tank_volume from rocketprops.rocket_prop import get_prop """ Calculate the required volume of a Hydrazine (N2H4) tank. Assume: required usable propellant is 50 kg vehicle max operating/storage/transport temperature is 50 deg C. minimum ullage volume is 3%. expulsion efficiency = 98%. """ pObj = get_prop('N2H4') cc_Total, kg_loaded, kg_residual = calc_tank_volume( pObj, kg_expelled=50.0, TmaxC=50.0, expPcent=98.0, ullPcent=3.0 ) print('cc_Total = %g cc'%cc_Total) print('loaded propellant mass = %g kg'%kg_loaded ) print('residual propellant mass = %g kg'%kg_residual ) ``` -------------------------------- ### Calculate Injector Orifice Flow Source: https://rocketprops.readthedocs.io/en/latest/_sources/examples.rst.txt Calculates injection velocity and mass flow rate for an injector orifice using rocketprops.injector_supt. ```python from rocketprops.rocket_prop import get_prop from rocketprops.injector_supt import calc_inj_velocity, calc_orifice_flow_rate """ Calculate the injection velocity of an injector orifice and its mass flow rate """ pObj = get_prop( 'N2O4' ) ft_per_sec = calc_inj_velocity( pObj, dPpsia=50.0, TdegR=530.0, Ppsia=1000.0) print( 'velocity =',ft_per_sec, 'ft/s' ) wdot = calc_orifice_flow_rate(pObj, CdOrf=0.75, DiamInches=0.01, dPpsia=50.0, TdegR=530.0, Ppsia=1000.0) print( 'Orifice flow rate =',wdot , 'lbm/sec' ) ``` -------------------------------- ### rocketprops.line_supt.calc_line_vel_dp Source: https://rocketprops.readthedocs.io/en/latest/functions.html Calculates the line velocity and pressure drop for a propellant line. ```APIDOC ## rocketprops.line_supt.calc_line_vel_dp(pObj, TdegR=530.0, Ppsia=1000.0, wdotPPS=0.5, IDinches=0.335, roughness=5e-06, Kfactors=2.0, len_inches=50.0) ### Description Calculate the line velocity and pressure drop in propellant line. ### Parameters - **pObj** (Propellant) - Required - propellant object - **TdegR** (float) - Optional - temperature of propellant, degR - **Ppsia** (float) - Optional - inlet pressure to orifice, psia - **wdotPPS** (float) - Optional - mass flow rate in line, lbm/sec - **IDinches** (float) - Optional - inside diameter of line, in - **roughness** (float) - Optional - line roughness, inches - **Kfactors** (float) - Optional - number of velocity heads lost due to bends, valves, etc. - **len_inches** (float) - Optional - length of line, inches ### Returns (float, float) - tuple of velocity and pressure drop (velFPS, deltaP), (ft/s, psid) ``` -------------------------------- ### rocketprops.valve_supt.kv_valve_dp Source: https://rocketprops.readthedocs.io/en/latest/functions.html Calculates the pressure drop for a valve using a metric flow coefficient (Kv). ```APIDOC ## rocketprops.valve_supt.kv_valve_dp(pObj, Kv=1.0, wdotPPS=0.5, TdegR=530.0, Ppsia=1000.0) ### Description Calculate valve pressure drop for a valve with a known metric flow coefficient, Kv. Metric flow coefficient (Kv) is the amount of water (in m^3/hr) at 4 degC that will flow through a fully open valve with a difference of 1 bar between the inlet and the outlet. ### Parameters - **pObj** (Propellant) - Required - Propellant object - **Kv** (float) - Optional - Valve flow coefficient - **wdotPPS** (float) - Optional - Propellant mass flow rate in line, lbm/sec - **TdegR** (float) - Optional - Propellant temperature, degR - **Ppsia** (float) - Optional - Propellant inlet pressure to valve, psia ### Returns - **float** - Propellant pressure drop, psid ``` -------------------------------- ### rocketprops.tank_supt.calc_tank_volume Source: https://rocketprops.readthedocs.io/en/latest/functions.html Calculates the required volume of a propellant tank based on mass, temperature, and efficiency requirements. ```APIDOC ## rocketprops.tank_supt.calc_tank_volume(pObj, kg_expelled=50.0, TmaxC=50.0, expPcent=98.0, ullPcent=3.0) ### Description Calculate the volume of a propellant tank given operating requirements. ### Parameters - **pObj** (Propellant) - Required - propellant object - **kg_expelled** (float) - Optional - mass of expelled propellant in kg - **TmaxC** (float) - Optional - max operating/storage/transport temperature in deg C - **expPcent** (float) - Optional - expulsion efficiency in percent - **ullPcent** (float) - Optional - percent of total tank volume that is ullage at TmaxC ### Returns (float, float, float) - (volume of tank (ml), loaded propellant mass (kg), residual propellant mass (kg)) ``` -------------------------------- ### rocketprops.injector_supt.calc_inj_velocity Source: https://rocketprops.readthedocs.io/en/latest/functions.html Calculates the injection velocity of a propellant based on pressure drop, temperature, and inlet pressure. ```APIDOC ## rocketprops.injector_supt.calc_inj_velocity(pObj, dPpsia=50.0, TdegR=530.0, Ppsia=1000.0) ### Description Calculate the injection velocity of a propellant. ### Parameters - **pObj** (Propellant) - Required - propellant object - **dPpsia** (float) - Optional - pressure drop across orifice, psid - **TdegR** (float) - Optional - temperature of propellant, degR - **Ppsia** (float) - Optional - inlet pressure to orifice, psia ### Returns - **velocity** (float) - injection velocity, ft/sec ``` -------------------------------- ### rocketprops.valve_supt.cv_valve_dp Source: https://rocketprops.readthedocs.io/en/latest/functions.html Calculates the pressure drop for a valve using an imperial flow coefficient (Cv). ```APIDOC ## rocketprops.valve_supt.cv_valve_dp(pObj, Cv=1.0, wdotPPS=0.5, TdegR=530.0, Ppsia=1000.0) ### Description Calculate valve pressure drop for a valve with a known imperial flow coefficient, Cv. Imperial flow coefficient (Cv) is the amount of water (in gallons per minute) at 60 degF that will flow through a fully open valve with a difference of 1 psi between the inlet and the outlet. ### Parameters - **pObj** (Propellant) - Required - Propellant object - **Cv** (float) - Optional - Valve flow coefficient - **wdotPPS** (float) - Optional - Propellant mass flow rate in line, lbm/sec - **TdegR** (float) - Optional - Propellant temperature, degR - **Ppsia** (float) - Optional - Propellant inlet pressure to valve, psia ### Returns - **float** - Propellant pressure drop, psid ``` -------------------------------- ### rocketprops.line_supt.calc_line_id_dp Source: https://rocketprops.readthedocs.io/en/latest/functions.html Calculates the inner diameter and pressure drop for a propellant line. ```APIDOC ## rocketprops.line_supt.calc_line_id_dp(pObj, TdegR=530.0, Ppsia=1000.0, wdotPPS=0.5, velFPS=13.0, roughness=5e-06, Kfactors=2.0, len_inches=50.0) ### Description Calculate the inner diameter and pressure drop in propellant line. ### Parameters - **pObj** (Propellant) - Required - propellant object - **TdegR** (float) - Optional - temperature of propellant, degR - **Ppsia** (float) - Optional - inlet pressure to orifice, psia - **wdotPPS** (float) - Optional - mass flow rate in line, lbm/sec - **velFPS** (float) - Optional - velocity of liquid in line, ft/sec - **roughness** (float) - Optional - line roughness, inches - **Kfactors** (float) - Optional - number of velocity heads lost due to bends, valves, etc. - **len_inches** (float) - Optional - length of line, inches ### Returns (float, float) - tuple of inside diameter and pressure drop (dinsid, deltaP), (inch, psid) ``` -------------------------------- ### rocketprops.injector_supt.calc_orifice_flow_rate Source: https://rocketprops.readthedocs.io/en/latest/functions.html Calculates the mass flow rate through a single injector orifice. ```APIDOC ## rocketprops.injector_supt.calc_orifice_flow_rate(pObj, CdOrf=0.75, DiamInches=0.01, dPpsia=50.0, TdegR=530.0, Ppsia=1000.0) ### Description Calculate mass flow rate through a single injector orifice. ### Parameters - **pObj** (Propellant) - Required - propellant object - **CdOrf** (float) - Optional - discharge coefficient of orifice - **DiamInches** (float) - Optional - diameter of orifice, inch - **dPpsia** (float) - Optional - pressure drop across orifice, psid - **TdegR** (float) - Optional - temperature of propellant, degR - **Ppsia** (float) - Optional - inlet pressure to orifice, psia ### Returns - **flow_rate** (float) - mass flow rate of single orifice, lbm/sec ``` -------------------------------- ### rocketprops.rocket_prop.get_prop Source: https://rocketprops.readthedocs.io/en/latest/functions.html Retrieves a Propellant object for a specified propellant name. ```APIDOC ## rocketprops.rocket_prop.get_prop(name, suppress_warning=False) ### Description Return a Propellant object for the named propellant. ### Parameters - **name** (string) - Required - Name of propellant (e.g., "N2O4" or "LOX") - **suppress_warning** (boolean) - Optional - If True, do not print warnings. ### Returns - **Propellant** (object) - Propellant object for the named propellant. ``` -------------------------------- ### rocketprops.rocket_prop.Propellant Source: https://rocketprops.readthedocs.io/en/latest/functions.html The Propellant class is the primary interface for modeling a specific liquid rocket propellant. It provides various methods to calculate thermodynamic and transport properties based on temperature or reduced temperature. ```APIDOC ## class rocketprops.rocket_prop.Propellant(name='MMH') ### Description Initializes a Propellant object for a given propellant name. ### Methods - **CondAtTdegR(TdegR)**: Returns thermal conductivity of saturated liquid in BTU/hr-ft-R given temperature in degR. - **CondAtTr(Tr)**: Returns thermal conductivity of saturated liquid in BTU/hr-ft-R given reduced temperature (Tr). - **CpAtTdegR(TdegR)**: Returns Heat Capacity of saturated liquid in BTU/lbm-R given temperature in degR. - **CpAtTr(Tr)**: Returns heat capacity of saturated liquid in BTU/lbm-R given reduced temperature (Tr). - **HvapAtTdegR(TdegR)**: Returns heat of vaporization of saturated liquid in BTU/lbm given temperature in degR. - **HvapAtTr(Tr)**: Returns heat of vaporization of saturated liquid in BTU/lbm given reduced temperature (Tr). - **P_data_range()**: Returns a tuple of the pressure range (Pmin, Pmax) in psia. - **PvapAtTdegR(TdegR)**: Returns saturation pressure in psia given temperature in degR. - **PvapAtTr(Tr)**: Returns vapor pressure of saturated liquid in psia given reduced temperature (Tr). - **SGLiqAtTdegR(TdegR)**: Returns specific gravity of saturated liquid in g/ml given temperature in degR. - **SGLiqAtTr(Tr)**: Returns specific gravity of saturated liquid in g/ml given reduced temperature (Tr). - **SGVapAtTdegR(TdegR)**: Returns specific gravity of Saturated Vapor in g/ml given temperature in degR. - **SGVapAtTr(Tr)**: Returns specific gravity of Saturated Vapor in g/ml given reduced temperature (Tr). - **SG_compressed(TdegR, Ppsia)**: Calculates compressed-liquid specific gravity in g/ml. - **SG_compressedCOSTALD(TdegR, Ppsia)**: Calculates compressed-liquid specific gravity using the COSTALD CSP method. - **SG_compressedCZ1(TdegR, Ppsia)**: Calculates compressed-liquid specific gravity using the Chang Zhao method. - **SG_compressedCZ2(TdegR, Ppsia)**: Calculates compressed-liquid specific gravity using the modified Chang Zhao method. - **SG_compressedNasrfar(TdegR, Ppsia)**: Calculates compressed-liquid specific gravity using the Nasrfar Moshfeghian method. ### Properties - **SGc**: Returns critical specific gravity. ``` === COMPLETE CONTENT === This response contains all available snippets from this library. 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