RocketProps

https://rocketprops.readthedocs.io/en/latest/
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RocketProps calculates the thermodynamic and transport properties of various liquid rocket...
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### 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
```

--------------------------------

### 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
```

--------------------------------

### 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()"
```

--------------------------------

### 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()
```
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