<?xml version="1.0"?>
<!-- Generated by Aero-Matic v 1.1

     Inputs:
                horsepower: 100
                     pitch: fixed
            max engine rpm: 5800
        prop diameter (ft): 4.9215

     Outputs:
              max prop rpm: 3812.46
                gear ratio:    1.52
                       Cp0: 0.031225
                       Ct0: 0.043715
       static thrust (lbs):  263.79
-->

<propeller version="1.01" name="prop">
  <ixx>   1.02 </ixx>
  <diameter unit="IN">  59.1 </diameter>
  <numblades> 3 </numblades>
  <gearratio>  1.52 </gearratio>
  <cp_factor> 1.00 </cp_factor>
  <ct_factor> 1.00 </ct_factor>

  <table name="C_THRUST" type="internal">
    <tableData>
       0.0   0.0476
       0.1   0.0457
       0.2   0.0437
       0.3   0.0402
       0.4   0.0361
       0.5   0.0318
       0.6   0.0257
       0.7   0.0195
       0.8   0.0106
       1.0  -0.0036
       1.2  -0.0188
       1.4  -0.0337
     </tableData>
  </table>


  <table name="C_POWER" type="internal">
    <tableData>
       0.0   0.0320
       0.1   0.0320
       0.2   0.0312
       0.3   0.0305
       0.4   0.0287
       0.5   0.0263
       0.6   0.0242
       0.7   0.0203
       0.8   0.0166
       1.0   0.0059
       1.2  -0.0095
       1.4  -0.0285
       1.6  -0.0483
     </tableData>
  </table>

  <!-- thrust effects of helical tip Mach -->
  <table name="CT_MACH" type="internal">
    <tableData>
    0.85   1.0
    1.05   0.8
  </tableData>
  </table>

  <!-- power-required effects of helical tip Mach -->
  <table name="CP_MACH" type="internal">
    <tableData>
    0.85   1.0
    1.05   1.8
    2.00   1.4
  </tableData>
  </table>

</propeller>