<?xml version="1.0"?>
<!--
 Source:
 "Evolution of Wright Flyer Propellers between 1903 and 1912"
 http://www.wrightexperience.com/pdfs/props.pdf

 "Wright propellers"
 http://www.slideshare.net/RolandBoucher/wright-propellers-rev3-16632071
 - Prop diameter            = 8.5 feet
 - Blade width at tip       = 8 inches
 - Blade twist at tip       = 1.66 degrees
 - Blade area               = 2 sq. ft.
 - Prop speed               = 245 Rpm
 - Speed at C.P.            = 61 mph
 - Normal pressure          = 12.4 lb./sq. ft.
 - Thrust                   = 18.75 lbs.
 - CL = 18.76/24.8          = 0.756
 - Angle of Airfoil #31     = 7.25 deg
 - Measured torque          = 3.5 lbs
 - Measured power           = 0.58 HP
 - L/D of propeller airfoil = 5.4

 1903 WrightFlyer propeller:
 90 lbs. of thrust at  an airspeed of 24 mph with a propeller speed of 330 rpm.
 Calculated torque force of 40 lbs requiring an 8.7. H.P. motor and an estimated
 downwash (throw down) of 7.7 fps, resulting in a pitch angle of 27 degrees to
 yield a 7 degree angle of incidence. Calculated efficiency is 66 percent.

 Tests on the 1903 flyer made in winds of 20 to 25 mph gave thrust at between
 120 lbs and 132 lbs. This was much higher than expected.

 Airpseed  Efficiency    Power    Thrust  Incidence
    24	     66         8.7@330	    90       7.0
   20-25     N/A         12@350    132       N/A
   20-25     N/A         12@350    120       N/A
    24       66          12@370    124      11.6
    30       75        10.6@370    99.8      8.6

 Also:
 http://www.wright-brothers.org/Information_Desk/Just_the_Facts/Engines_&_Props/1903_Props.htm
-->
 

<!-- this version models both propellers -->
<propeller name="wright1903_propellers" version="1.01">
  <ixx>  12.07 </ixx>
  <diameter unit="IN"> 102.0 </diameter>		<!-- Flyer -->
  <numblades> 4 </numblades>				<!-- Flyer -->
  <gearratio>  2.8824 </gearratio>			<!-- Flyer -->
  <p_factor>   8.06 </p_factor>

  <table name="C_THRUST" type="internal">		<!-- aeromatic -->
     <tableData>
       0.0   0.0204
       0.1   0.0196
       0.2   0.0188
       0.3   0.0173
       0.4   0.0155
       0.5   0.0137
       0.6   0.0110
       0.7   0.0084
       0.8   0.0045
       1.0  -0.0015
       1.2  -0.0080
       1.4  -0.0145
     </tableData>
  </table>

  <table name="C_POWER" type="internal">		<!-- aeromatic -->
     <tableData>
       0.0   0.0013
       0.1   0.0013
       0.2   0.0013
       0.3   0.0012
       0.4   0.0012
       0.5   0.0011
       0.6   0.0010
       0.7   0.0008
       0.8   0.0007
       1.0   0.0002
       1.2  -0.0004
       1.4  -0.0011
       1.6  -0.0019
     </tableData>
  </table>

</propeller>

