<?xml version="1.0"?>
<rocket_engine name="Estes E-9">
  <!--
  -->

  <isp> 244 </isp>
  <builduptime> 0.15 </builduptime>
  <thrust_table name="propulsion/thrust_prop_remain" type="internal">
    <tableData> <!--
      =========  =========  ===========  ========= =====
      Prop Burn   Thrust    Total Impls    wdot     Time
      (Wt, lbs)   (lbf)       (lbf-sec)  (lbf/sec) (sec)
      =========  =========  ===========  ========= =====  -->
       0.00000,  0.02108 <!-- 0.00000,   0.00009,  0.0000 -->
       0.00002,  0.21044 <!-- 0.00469,   0.00086,  0.0406 -->
       0.00022,  1.62214 <!-- 0.05456,   0.00665,  0.0950 -->
       0.00072,  3.72941 <!-- 0.17671,   0.01529,  0.1406 -->
       0.00105,  4.82523 <!-- 0.25520,   0.01978,  0.1590 -->
       0.00161,  5.33086 <!-- 0.39301,   0.02185,  0.1861 -->
       0.00182,  5.62586 <!-- 0.44281,   0.02306,  0.1952 -->
       0.00223,  5.62573 <!-- 0.54402,   0.02306,  0.2132 -->
       0.00243,  5.41491 <!-- 0.59332,   0.02220,  0.2221 -->
       0.00326,  3.62315 <!-- 0.79401,   0.01485,  0.2665 -->
       0.00368,  2.94850 <!-- 0.89672,   0.01209,  0.2978 -->
       0.00423,  2.52664 <!-- 1.03182,   0.01036,  0.3471 -->
       0.00495,  2.33645 <!-- 1.20665,   0.00958,  0.4190 -->
       0.00587,  2.23037 <!-- 1.43252,   0.00914,  0.5180 -->
       0.00755,  2.20800 <!-- 1.84174,   0.00905,  0.7024 -->
       0.01617,  2.15909 <!-- 3.94340,   0.00885,  1.6649 -->
       0.02565,  2.10932 <!-- 6.25675,   0.00865,  2.7488 -->
       0.02616,  2.10891 <!-- 6.38007,   0.00865,  2.8073 -->
       0.02646,  2.06651 <!-- 6.45517,   0.00847,  2.8432 -->
       0.02675,  0.78053 <!-- 6.52501,   0.00320,  2.8923 -->
       0.02678,  0.16921 <!-- 6.53346,   0.00069,  2.9101 -->
       0.02679,  0.00051 <!-- 6.53460,   0.00000,  2.9235 -->
       0.02679,  0.00000 <!-- 6.53460,   0.00000,  2.9300 -->
    </tableData>
  </thrust_table>
</rocket_engine>
