<?xml version="1.0"?>
<!-- Generated by Aero-Matic v 0.7
     Date: 10 August 2005
     Version: 1.1

     Inputs:
       horsepower:   1600.0
       pitch:        variable

     Outputs:
       linear-blade-inches: 212


  References :
  ==========
  - http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet
  (FAA certificate, TC704 - 25 january 1939, B-314) :

  Engine limits : * maximum except take-off (straight line manifold pressure variation) : 33.2 in. hg. 2100 rpm (1200 hp)
                  at 5400 ft, 35.0 in. hg. 2100 rpm (1200 hp) at sea level.
                  * take-off (2 minutes), 42.5 in. hg. 2400 rpm (1550 hp).

  Propeller : * Hamilton standard 3 blade constant speed, 6243A-3 to 6243A-6 inclusive, diameter 14'9-3/8" maximum
              14'5-5/8" minimum (1928 lb).
              * Hamilton standard 3 blade constant speed, 6159A-0 to 6159A-3 inclusive, diameter 14'3/8" maximum
              13'8-3/4" minimum (1819 lb).

  - http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet
  (FAA certificate, TC704 - 2 may 1941 B-314A) :

  Engine limits : * maximum except take-off (straight line manifold pressure variation) : 35.8 in. hg. 2300 rpm (1350 hp)
                  at 6200 ft, 37.5 in. hg. 2300 rpm (1350 hp) at sea level.
                  * take-off (2 minutes), 43.5 in. hg. 2400 rpm (1600 hp).

  Propeller : Hamilton standard 3 blade constant speed, 6243A-3 to 6243A-6 inclusive, diameter 14'9-3/8" maximum
              14'5-5/8" minimum (1928 lb).

  - http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet
  (FAA certificate, TC176 - Wright Double row Cyclone GR-260025) :

  16:9 or 16:7 reduction gears.


  J above 1.0 :
  ===========
  - http://naca.larc.nasa.gov/reports/1938/naca-report-640/ :
    The aerodynamics characteristics of full-scale propellers having 2, 3, and 4 blades of Clark Y and R.A.F. 6
    airfoil sections, Edwin P. Hartman and David Biermann, NACA 640, 1938.

  - http://naca.larc.nasa.gov/reports/1953/naca-tn-2966/ :
    Propeller-performance charts for transport airplanes, Jean Gilman, NACA 2966, July 1953.

  - http://naca.larc.nasa.gov/reports/1954/naca-tn-3228/ :
    Aerodynamic investigation of a four-blade propeller operating through an angle of attack range from 0 to 180 deg,
    H. Clyde McLemore and Michael D. Cannon, NACA 3228, June 1954.

-->

<!-- choiced a propeller of B-314 A. -->

<propeller name="Hamilton Standard 6243A-3">

  <!-- Gear ratio 1 :
       ============

       14.5 ft diameter :
       - with 75 in., not enough power to climb at full load.
       - multiply the aeromatic moment by 2.32 ^2 = 174/75 ^2.

       is a constant speed propeller because of 700-2400.

       thrust x 0.4, power x 0.2, 700 - 2400 rpm (propeller).

       Reduction gear ratio 16/9 :
       =========================

       divide min/max rpm (700/2400) by the gear ratio 1.778.
  -->

  <ixx> 20.405 </ixx>                                                       <!-- aeromatic 3.7910590942383 -->
  <diameter unit="IN"> 174.0 </diameter>                                    <!-- aeromatic 75 -->
  <numblades> 3 </numblades>                                                <!-- aeromatic 4 -->
  <gearratio> 1.778 </gearratio>                                            <!-- aeromatic none (1.0) -->
  <minpitch> 10 </minpitch>
  <maxpitch> 30 </maxpitch>
  <minrpm> 394 </minrpm>
  <maxrpm> 1350 </maxrpm>                                                   <!-- aeromatic 2700 -->


<!--=== gear ratio 16/9 (J above 1.0) === -->

<!-- multiply by 0.9 :
     - cut 10 at 0.4, then patch X 0.3 until 1.0 (deceleration at landing). 
     - split 30 to 2.0.
-->

  <table name="C_THRUST" type="internal">
    <tableData>
           10      30
      0.0  0.06739 0.0842
      0.1  0.06674 0.0838
      0.2  0.06610 0.0834
      0.3  0.06545 0.0830
      0.4  0.05963 0.0826
      0.5  0.01771 0.0822
      0.6  0.01512 0.0818
      0.7  0.01176 0.0782
      0.8  0.00864 0.0745
      0.9  0.00480 0.0705
      1.0  0.00096 0.0664
      1.2  0.00000 0.0567
      1.4  0.00000 0.0441
      1.6  0.00000 0.0324
      1.8  0.00000 0.0180
      2.0  0.00000 0.0036
    </tableData>
  </table>

<!-- multiply by 0.9, cut 10 at 1.0, split 30 to 2.0 : too much thrust at landing (empty load).

     max full load 9000 ft : 170 kt.
     max empty load 13400 ft : 160 kt.
-->

<!--
  C_THRUST   16 2
       10      30
  0.0  0.06739 0.0842
  0.1  0.06674 0.0838
  0.2  0.06610 0.0834
  0.3  0.06545 0.0830
  0.4  0.05963 0.0826
  0.5  0.05314 0.0822
  0.6  0.04536 0.0818
  0.7  0.03528 0.0782
  0.8  0.02592 0.0745
  0.9  0.01440 0.0705
  1.0  0.00288 0.0664
  1.2  0.00000 0.0567
  1.4  0.00000 0.0441
  1.6  0.00000 0.0324
  1.8  0.00000 0.0180
  2.0  0.00000 0.0036
-->

<!-- multiply by 0.8, cut 10 at 1.0, split 30 to 2.0 :

     max full load 9000 ft : 161 kt.
     max empty load 13400 ft : 154 kt.
-->

<!--
  C_THRUST   16 2
       10      30
  0.0  0.05990 0.0749
  0.1  0.05933 0.0746
  0.2  0.05875 0.0742
  0.3  0.05818 0.0738
  0.4  0.05300 0.0734
  0.5  0.04723 0.0731
  0.6  0.04032 0.0727
  0.7  0.03136 0.0695
  0.8  0.02304 0.0662
  0.9  0.01280 0.0626
  1.0  0.00256 0.0590
  1.2  0.00000 0.0504
  1.4  0.00000 0.0392
  1.6  0.00000 0.0288
  1.8  0.00000 0.0160
  2.0  0.00000 0.0032
-->

<!-- multiply by 0.3 : for patching -->

<!--
  C_THRUST   6 1
       10
  0.5  0.01771
  0.6  0.01512
  0.7  0.01176
  0.8  0.00864
  0.9  0.00480
  1.0  0.00096
-->

<!-- multiply by 0.5 : cut 10 at 1.0, split 30 to 2.0.

     solve the engine stop by low pressure.
-->

  <table name="C_POWER" type="internal">
    <tableData>
             10      30
        0.0  0.01144 0.05198
        0.1  0.01126 0.05159
        0.2  0.01109 0.05119
        0.3  0.01074 0.05080
        0.4  0.01040 0.05040
        0.5  0.01005 0.04962
        0.6  0.00953 0.04883
        0.7  0.00832 0.04804
        0.8  0.00658 0.04725
        0.9  0.00433 0.04647
        1.0  0.00173 0.04568
        1.2  0.00000 0.04331
        1.4  0.00000 0.03780
        1.6  0.00000 0.02993
        1.8  0.00000 0.01969
        2.0  0.00000 0.00788
    </tableData>
  </table>


<!--=== backup gear ratio 16/9 (split method) === -->

<!-- multiply by 1.75, cut 10 at 1.0, split 30 to 2.0 : above 180 kt a 9500 ft full load. 
     engine may stop at idle on ground, whatever the pitch (low atmospheric pressure).
-->

<!--
  C_THRUST   16 2
       10      30
  0.0  0.13104 0.1638
  0.1  0.12978 0.1630
  0.2  0.12852 0.1622
  0.3  0.12726 0.1615
  0.4  0.11594 0.1607
  0.5  0.10332 0.1599
  0.6  0.08820 0.1591
  0.7  0.06860 0.1520
  0.8  0.05040 0.1449
  0.9  0.02800 0.1371
  1.0  0.00560 0.1292
  1.2  0.00000 0.1103
  1.4  0.00000 0.0858
  1.6  0.00000 0.0630
  1.8  0.00000 0.0350
  2.0  0.00000 0.0070
-->

<!-- multiply by 1.0, cut 10 at 1.0, split 30 to 2.0.
     engine may stop at idle on ground, whatever the pitch (low atmospheric pressure).
-->

<!--
  C_POWER   16 2
       10      30
  0.0  0.02287 0.10395
  0.1  0.02252 0.10316
  0.2  0.02217 0.10237
  0.3  0.02148 0.10159
  0.4  0.02079 0.10080
  0.5  0.02009 0.09923
  0.6  0.01905 0.09765
  0.7  0.01663 0.09608
  0.8  0.01316 0.09450
  0.9  0.00866 0.09293
  1.0  0.00346 0.09135
  1.2  0.00000 0.08662
  1.4  0.00000 0.07560
  1.6  0.00000 0.05985
  1.8  0.00000 0.03937
  2.0  0.00000 0.01575
-->


<!-- === backup gear ratio 1.0 === -->

<!-- - multiply by 0.4, to get the thrust of takeoff (minimum pitch).
     - with 492 lb X 2 engines (2 stopped), hull drag can stop alone the taxi (no brake) : maximum pitch.
-->
<!--
  C_THRUST   11 2
       10      30
  0.0  0.02995 0.03744
  0.1  0.02966 0.03708
  0.2  0.02938 0.03672
  0.3  0.02909 0.03636
  0.4  0.02650 0.03312
  0.5  0.02362 0.02952
  0.6  0.02016 0.02520
  0.7  0.01568 0.01960
  0.8  0.01152 0.01440
  0.9  0.00640 0.00800
  1.0  0.00120 0.00160
-->

<!-- - multiply by 0.2 : 2500 RPM max at sea level, with minimum pitch.
     - 700 RPM idle at sea level, with maximum pitch.
-->

<!--
  C_POWER   11 2
       10      30
  0.0  0.00457 0.02079
  0.1  0.00450 0.02047
  0.2  0.00443 0.02016
  0.3  0.00430 0.01953
  0.4  0.00416 0.01890
  0.5  0.00402 0.01827
  0.6  0.00381 0.01732
  0.7  0.00333 0.01512
  0.8  0.00263 0.01197
  0.9  0.00173 0.00787
  1.0  0.00069 0.00315
-->


<!-- === backup of aeromatic tables === -->

<!--
  C_THRUST   11 2
       10      30
  0.0  0.07488 0.0936
  0.1  0.07416 0.0927
  0.2  0.07344 0.0918
  0.3  0.07272 0.0909
  0.4  0.06625 0.0828
  0.5  0.05904 0.0738
  0.6  0.05040 0.0630
  0.7  0.03920 0.0490
  0.8  0.02880 0.0360
  0.9  0.01600 0.0200
  1.0  0.00320 0.0040
  C_POWER   11 2
       10      30
  0.0  0.02287 0.10395
  0.1  0.02252 0.10237
  0.2  0.02217 0.10080
  0.3  0.02148 0.09765
  0.4  0.02079 0.09450
  0.5  0.02009 0.09135
  0.6  0.01905 0.08662
  0.7  0.01663 0.07560
  0.8  0.01316 0.05985
  0.9  0.00866 0.03937
  1.0  0.00346 0.01575
-->

</propeller>


