<?xml version="1.0"?>

<!--
**************************************************************************

Copyright (c) 2016 Simon 'bomber' Morley
simonbomber64 at googlemail.com

This work is licensed under the 
Creative Commons Attribution-NonCommercial-ShareAlike 3.0 Unported License. 
To view a copy of this license, 
visit http://creativecommons.org/licenses/by-nc-sa/3.0/ or 
send a letter to Creative Commons, PO Box 1866, Mountain View, CA 94042, USA.

Attribution,  You must give appropriate credit, provide a link to the license, 
and indicate if changes were made. You may do so in any reasonable manner, 
but not in any way that suggests the licensor endorses you or your use.

NonCommercial,  You may not use the material for commercial purposes.

ShareAlike,  If you remix, transform, or build upon the material, 
you must distribute your contributions under the same license as the original. 

**************************************************************************


Based on tables from JavaProp.


 -->

<propeller name="McCauley 1A105-SCM 7053, 70inch 2-blade aluminum prop. (Fixed pitch)">

	
	<ixx unit="SLUG*FT2"> 1.77 </ixx>
	
	<!-- 
	Prop Characteristics
	-->

	<diameter unit="IN">  70 </diameter>
	<numblades> 2 </numblades>
 	<constspeed> 0 </constspeed>
	
	<!-- 
	<gearratio> is the gearing between the prop and the engine,
	Normally it's defined from the engine to the propeller and is a value below zero
	ie 0.78
	To specify from the propeller to the engine use 1/X = gearration = 1/0.78 = 1.28
	--> 
  

	<gearratio>  1.0 </gearratio>
  
  
	<!-- 
	<ct_factor> is the props co-efficent of thrust 'tuning' factor
	<cp_factor> is the props co-efficent of power 'tuning' factor
	-->
	<ct_factor> 1.0 </ct_factor>
	<cp_factor> 1.0 </cp_factor>
  

	<table name="C_THRUST" type="internal">
		<tableData>
			0.00	0.126847
			0.05	0.119041
			0.10	0.125292
			0.15	0.122432
			0.20	0.118955
			0.25	0.114345
			0.30	0.108913
			0.35	0.102908
			0.40	0.096132
			0.45	0.088391
			0.50	0.080358
			0.55	0.072039
			0.60	0.063445
			0.65	0.054722
			0.70	0.045755
			0.75	0.036546
			0.80	0.027116
			0.85	0.017478
			0.90	0.007646
			0.95	-0.002453
			1.00	-0.012552
			1.05	-0.022384
			1.10	-0.032022
			1.15	-0.041452
			1.20	-0.050661
			1.25	-0.059628
			1.30	-0.068351
			1.35	-0.076945
			1.40	-0.085264
			1.45	-0.093297
			1.50	-0.101038
			1.55	-0.107814
			1.60	-0.113819
			1.65	-0.119251
			1.70	-0.123861
		</tableData>
	</table>


	<table name="C_POWER" type="internal">
		<tableData>
			0.00	0.05781
			0.05	0.059132
			0.10	0.05871
			0.15	0.059698
			0.20	0.060591
			0.25	0.061084
			0.30	0.06112
			0.35	0.060727
			0.40	0.059689
			0.45	0.057823
			0.50	0.055381
			0.55	0.052326
			0.60	0.04861
			0.65	0.044264
			0.70	0.039201
			0.75	0.033377
			0.80	0.026766
			0.85	0.019339
			0.90	0.011073
			0.95	0.001869
			1.00	-0.007335
			1.05	-0.015601
			1.10	-0.023028
			1.15	-0.029639
			1.20	-0.035463
			1.25	-0.040526
			1.30	-0.044872
			1.35	-0.048588
			1.40	-0.051643
			1.45	-0.054085
			1.50	-0.055951
			1.55	-0.056989
			1.60	-0.057382
			1.65	-0.057346
			1.70	-0.056853
		</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
		</tableData>
	</table>

</propeller>
