.. a50_prop

A50
===


`Aerozine-50 <https://en.wikipedia.org/wiki/Aerozine_50>`_
is a 50-50 mixture of hydrazine and UDMH developed by Aerojet.
It was used in the 
`Delta second stage <http://www.astronautix.com/d/delta.html>`_ , the
`Apollo lunar lander <http://www.astronautix.com/a/apollolm.html>`_ and in
`many other vehicles <http://www.astronautix.com/n/n2o4aerozine-50.html>`_



Reference Points
----------------

A50 == 50% N2H4 + 50% UDMH == Aerozine50




`Hover over column headers to see definitions, values to see alternate units`

.. raw:: html

    <table width="100%">
    <tr><th></th>
        <th title="Reference Temperature">Tref</th>
        <th title="Reference Pressure">Pref</th>
        <th title="Specific Gravity">SG</th>
        <th title="Specific Heat">Cp</th>
        <th title="Heat of Vaporization">dHvap</th>
        <th title="Viscosity">Visc</th>
        <th title="Thermal Conductivity">Cond</th>
        <th title="Surface Tension">Surf</th>
    <tr><th>Source</th><th>R</th><th>psia</th><th>g/ml</th><th>BTU/lbm-R</th><th>BTU/lbm</th><th>poise</th><th>BTU/hr-ft-R</th><th>lbf/in</th></tr>


    <tr  style="background-color:#FFFF00"><td><a class="reference external" href="https://pypi.python.org/pypi/rocketprops">RocketProps</a></td><td  title="527.67 degR
    293.15 degK
    68 degF
    20 degC">527.7</td><td  title="14.6959 psia
    0.999997 atm
    1.01325 bar
    0.101325 MPa">14.7</td><td  title="0.903547 SG
    56.4066 lbm/ft**3
    0.0326427 lbm/inch**3
    903.547 kg/m**3">0.9035</td><td  title="0.728232 BTU/lbm/F
    0.72872 cal/g/C
    0.00072872 kcal/g/C
    3048.96 J/kg/K">0.728</td><td  title="346.5 BTU/lbm
    192.629 cal/g
    0.192629 kcal/g
    805.959 J/g">346.5</td><td  title="0.00920868 poise
    0.920868 cpoise
    0.000920868 Pa*s
    5.15662e-05 lbm/s/inch
    0.185638 lbm/hr/inch
    3.31513 kg/hr/m
    0.0331513 kg/hr/cm">9.209e-03</td><td  title="0.166107 BTU/hr/ft/delF
    3.84506e-06 BTU/s/inch/delF
    0.000687109 cal/s/cm/delC
    0.0687109 cal/s/m/delC
    0.00287486 W/cm/delC">0.1661</td><td  title="0.000169873 lbf/in
    0.0297493 N/m
    29.7493 mN/m
    29.7493 dyne/cm">1.699e-04</td></tr>
    <tr ><td><a class="reference external" href="./_static/AFRPL-TR-69-149Hydrazine fuels.pdf">AFRPL-TR-69-149</a></td><td  title="536.4 degR
    298 degK
    76.73 degF
    24.85 degC">536.4</td><td  title="14.7 psia
    1.00028 atm
    1.01353 bar
    0.101353 MPa">14.7</td><td  title="0.8987 SG
    56.104 lbm/ft**3
    0.0324676 lbm/inch**3
    898.7 kg/m**3">0.8987</td><td  title="0.732 BTU/lbm/F
    0.73249 cal/g/C
    0.00073249 kcal/g/C
    3064.74 J/kg/K">0.732</td><td  title="346.3 BTU/lbm
    192.518 cal/g
    0.192518 kcal/g
    805.494 J/g">346.3</td><td  title="0.00809 poise
    0.809 cpoise
    0.000809 Pa*s
    4.53019e-05 lbm/s/inch
    0.163087 lbm/hr/inch
    2.9124 kg/hr/m
    0.029124 kg/hr/cm">8.090e-03</td><td  title="0.165113 BTU/hr/ft/delF
    3.82207e-06 BTU/s/inch/delF
    0.000683 cal/s/cm/delC
    0.0683 cal/s/m/delC
    0.00285767 W/cm/delC">0.1651</td><td  title="0.000166167 lbf/in
    0.0291002 N/m
    29.1002 mN/m
    29.1002 dyne/cm">1.662e-04</td></tr>
    <tr ><td><a class="reference external" href="./_static/Aerojet_Propellant_Properties.pdf">Aerojet</a></td><td  title="527.67 degR
    293.15 degK
    68 degF
    20 degC">527.7</td><td  title="14.6959 psia
    0.999997 atm
    1.01325 bar
    0.101325 MPa">14.7</td><td  title="0.903547 SG
    56.4066 lbm/ft**3
    0.0326427 lbm/inch**3
    903.547 kg/m**3">0.9035</td><td  title="0.728304 BTU/lbm/F
    0.728792 cal/g/C
    0.000728792 kcal/g/C
    3049.26 J/kg/K">0.728</td><td  title="346.5 BTU/lbm
    192.629 cal/g
    0.192629 kcal/g
    805.959 J/g">346.5</td><td  title="0.00920872 poise
    0.920872 cpoise
    0.000920872 Pa*s
    5.15664e-05 lbm/s/inch
    0.185639 lbm/hr/inch
    3.31514 kg/hr/m
    0.0331514 kg/hr/cm">9.209e-03</td><td  title="0.165938 BTU/hr/ft/delF
    3.84115e-06 BTU/s/inch/delF
    0.000686411 cal/s/cm/delC
    0.0686411 cal/s/m/delC
    0.00287194 W/cm/delC">0.1659</td><td >---</td></tr>
    <tr ><td><a class="reference external" href="./_static/Vandenberg_Corrected_Properties.pdf">Vandenberg</a></td><td  title="527.67 degR
    293.15 degK
    68 degF
    20 degC">527.7</td><td  title="14.7 psia
    1.00028 atm
    1.01353 bar
    0.101353 MPa">14.7</td><td  title="0.90331 SG
    56.3918 lbm/ft**3
    0.0326341 lbm/inch**3
    903.31 kg/m**3">0.9033</td><td >---</td><td  title="368.379 BTU/lbm
    204.792 cal/g
    0.204792 kcal/g
    856.849 J/g">368.4</td><td >---</td><td  title="0.165916 BTU/hr/ft/delF
    3.84065e-06 BTU/s/inch/delF
    0.000686322 cal/s/cm/delC
    0.0686322 cal/s/m/delC
    0.00287157 W/cm/delC">0.1659</td><td >---</td></tr>

    </table>





Fluid Properties
----------------

A50 == 50% N2H4 + 50% UDMH == Aerozine50




`Hover over column headers to see definitions, values to see alternate units`

.. raw:: html

    <table width="100%">
    <tr><th></th>
        <th title="Molecular Weight">MolWt</th>
        <th title="Critical Temperature">Tc</th>
        <th title="Critical Pressure">Pc</th>
        <th title="Critical Density">SGc</th>
        <th title="Critical Compressibility Factor">Zc</th>
        <th title="Normal Boiling Point">Tnbp</th>
        <th title="Melting/Freezing Point">Tmelt</th>
        <th title="Pitzer Acentric Factor">omega</th></tr>
    <tr><th>Source</th><th>g/gmole</th><th>R</th><th>psia</th><th>g/ml</th><th>(-)</th><th>R</th><th>R</th><th>(-)</th></tr>


    <tr  style="background-color:#FFFF00"><td><a class="reference external" href="https://pypi.python.org/pypi/rocketprops">RocketProps</a></td><td>41.802</td><td  title="1092.67 degR
    607.039 degK
    633 degF
    333.889 degC">1092.7</td><td  title="1731 psia
    117.788 atm
    119.348 bar
    11.9348 MPa">1731.0</td><td  title="0.308661 SG
    19.2691 lbm/ft**3
    0.0111511 lbm/inch**3
    308.661 kg/m**3">0.3087</td><td>0.3203</td><td  title="617.67 degR
    343.15 degK
    158 degF
    70 degC">617.7</td><td  title="481.67 degR
    267.594 degK
    22 degF
    -5.55556 degC">481.7</td><td>0.16665</td></tr>
    <tr ><td><a class="reference external" href="./_static/AFRPL-TR-69-149Hydrazine fuels.pdf">AFRPL-TR-69-149</a></td><td>41.805</td><td  title="1093 degR
    607.222 degK
    633.33 degF
    334.072 degC">1093.0</td><td  title="1731 psia
    117.788 atm
    119.348 bar
    11.9348 MPa">1731.0</td><td >---</td><td>---</td><td  title="618 degR
    343.333 degK
    158.33 degF
    70.1833 degC">618.0</td><td  title="481.7 degR
    267.611 degK
    22.03 degF
    -5.53889 degC">481.7</td><td>---</td></tr>
    <tr ><td><a class="reference external" href="./_static/Aerojet_Propellant_Properties.pdf">Aerojet</a></td><td>41.802</td><td  title="1092.67 degR
    607.039 degK
    633 degF
    333.889 degC">1092.7</td><td  title="1731 psia
    117.788 atm
    119.348 bar
    11.9348 MPa">1731.0</td><td  title="0.308661 SG
    19.2691 lbm/ft**3
    0.0111511 lbm/inch**3
    308.661 kg/m**3">0.3087</td><td>0.3203</td><td  title="617.67 degR
    343.15 degK
    158 degF
    70 degC">617.7</td><td  title="481.67 degR
    267.594 degK
    22 degF
    -5.55556 degC">481.7</td><td>0.19047</td></tr>
    <tr ><td><a class="reference external" href="./_static/Vandenberg_Corrected_Properties.pdf">Vandenberg</a></td><td>41.802</td><td  title="1067.4 degR
    593 degK
    607.73 degF
    319.85 degC">1067.4</td><td  title="1359.38 psia
    92.5 atm
    93.7256 bar
    9.37256 MPa">1359.4</td><td  title="0.31 SG
    19.3527 lbm/ft**3
    0.0111995 lbm/inch**3
    310 kg/m**3">0.3100</td><td>0.2564</td><td  title="630 degR
    350 degK
    170.33 degF
    76.85 degC">630.0</td><td  title="478.8 degR
    266 degK
    19.13 degF
    -7.15 degC">478.8</td><td>0.39600</td></tr>

    </table>



The Aerojet and AFRPL-TR-69-149 data are virtually identical, perhaps indicating a
common source.



Vapor Pressure
--------------




.. raw:: html

    <div class="columns">
        <div style="width:75%;float:left" >
    
.. image:: ./_static/A50_Psat.png
   :target: ./_static/A50_Psat.png
    

.. raw:: html

    </div><div ><br><br>

| RocketProps Selected Curve
| :ref:`Aerojet Source`
| :ref:`AFRPL-TR-69-149 Source`
| :ref:`Vandenberg Source`
| :ref:`Wagner Fit Source`


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    </div></div>
    <div style="clear:both"></div>

    
`Click Image to View Fill Size`


Density
-------




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.. image:: ./_static/A50_SG.png
   :target: ./_static/A50_SG.png
    

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    </div><div ><br><br>

| RocketProps Selected Curve
| :ref:`Aerojet Source`
| :ref:`AFRPL-TR-69-149 Source`
| :ref:`Vandenberg Source`
| :ref:`Rocketdyne Source`
| :ref:`Rackett Scaling Source`


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    </div></div>
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Heat Capacity
-------------




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.. image:: ./_static/A50_Cp.png
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    </div><div ><br><br>

| RocketProps Selected Curve
| :ref:`Aerojet Source`
| :ref:`Joback Source`
| :ref:`AFRPL-TR-69-149 Source`


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    </div></div>
    <div style="clear:both"></div>

    
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Viscosity
---------




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.. image:: ./_static/A50_Visc.png
   :target: ./_static/A50_Visc.png
    

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    </div><div ><br><br>

| RocketProps Selected Curve
| :ref:`Aerojet Source`
| :ref:`Squires Source`
| :ref:`AFRPL-TR-69-149 Source`


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    </div></div>
    <div style="clear:both"></div>

    
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Heat of Vaporization
--------------------




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.. image:: ./_static/A50_Hvap.png
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| RocketProps Selected Curve
| :ref:`Aerojet Source`
| :ref:`Pitzer Hvap Source`
| :ref:`Vandenberg Source`


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    </div></div>
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Thermal Conductivity
--------------------




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.. image:: ./_static/A50_Cond.png
   :target: ./_static/A50_Cond.png
    

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    </div><div ><br><br>

| RocketProps Selected Curve
| :ref:`Aerojet Source`
| :ref:`Nicola Source`
| :ref:`AFRPL-TR-69-149 Source`
| :ref:`Vandenberg Source`


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    </div></div>
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`Click Image to View Fill Size`



Surface Tension
---------------

    

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.. image:: ./_static/A50_Surf.png
   :target: ./_static/A50_Surf.png
    

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    </div><div ><br><br>

| RocketProps Selected Curve
| :ref:`AFRPL-TR-69-149 Source`
| :ref:`Sastri-Rao Source`
| :ref:`Pitzer Surf Source`


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    </div></div>
    <div style="clear:both"></div>

    
`Click Image to View Fill Size`