commit e917d5de0da806b00a51a90319a6746ad941ad17
Author: rjensen <wino@jentronics.com>
Date:   Sat Feb 9 08:58:29 2013 -0700

    Raise idle manifold pressure on several JSBSim aircraft engines.

diff --git a/Aircraft/Aerocar/Engines/Lycoming_O-290.xml b/Aircraft/Aerocar/Engines/Lycoming_O-290.xml
index 7aff18d..ef3db35 100644
--- a/Aircraft/Aerocar/Engines/Lycoming_O-290.xml
+++ b/Aircraft/Aerocar/Engines/Lycoming_O-290.xml
@@ -14,17 +14,17 @@
 -->
 
 <piston_engine name="Lycoming_O-290">
-  <minmp unit="INHG">          6.0   </minmp>			<!-- unknown -->
-  <maxmp unit="INHG">         29.9   </maxmp>			<!-- unknown -->
+  <minmp unit="INHG">         10.1   </minmp>			<!-- unknown -->
+  <maxmp unit="INHG">         28.0   </maxmp>			<!-- unknown -->
   <displacement unit="IN3">  289.0   </displacement>
   <bore unit="IN">             4.875 </bore>
   <stroke unit="IN">           3.875 </stroke>
   <cylinders>                  4     </cylinders>
   <compression-ratio>          7.5   </compression-ratio>
-  <maxhp>       		     140.8   </maxhp>
-  <cycles>       			   4.0   </cycles>
-  <idlerpm>    		     	 700.0   </idlerpm>			<!-- unknown -->
-  <maxrpm>    		  	    2800.0   </maxrpm>
-  <maxthrottle>  		       1.0   </maxthrottle>
-  <minthrottle>  		       0.1   </minthrottle>
+  <maxhp>       	     140.8   </maxhp>
+  <cycles>       	       4.0   </cycles>
+  <idlerpm>        	     700.0   </idlerpm>			<!-- unknown -->
+  <maxrpm>    		    2800.0   </maxrpm>
+  <maxthrottle>  	       1.0   </maxthrottle>
+  <minthrottle>  	       0.1   </minthrottle>
 </piston_engine>
diff --git a/Aircraft/Boeing314/Engines/WrightGR-2600.xml b/Aircraft/Boeing314/Engines/WrightGR-2600.xml
index d3ae565..fa48bb4 100644
--- a/Aircraft/Boeing314/Engines/WrightGR-2600.xml
+++ b/Aircraft/Boeing314/Engines/WrightGR-2600.xml
@@ -60,7 +60,7 @@
      -  6 PSI for 35.8 inhg max at 2300 RPM, 6200 ft.
 -->
 
-   <minmp unit="INHG"> 6.0 </minmp>
+   <minmp unit="INHG"> 10.0 </minmp>
    <maxmp unit="INHG"> 43.5 </maxmp>                        <!-- aeromatic 30.0 -->
    <displacement unit="IN3"> 2603.00 </displacement>
    <bore unit="IN">6.125</bore>
diff --git a/Aircraft/Dragonfly/Engines/Rotax582.xml b/Aircraft/Dragonfly/Engines/Rotax582.xml
index c70be52..f67a680 100644
--- a/Aircraft/Dragonfly/Engines/Rotax582.xml
+++ b/Aircraft/Dragonfly/Engines/Rotax582.xml
@@ -9,8 +9,8 @@
     reference: http://de.wikipedia.org/wiki/Rotax_582
 -->
 <piston_engine name="Rotax582">
-  <minmp unit="INHG">          2.1 </minmp>
-  <maxmp unit="INHG">         30.0 </maxmp>
+  <minmp unit="INHG">          7.5 </minmp>
+  <maxmp unit="INHG">         28.0 </maxmp>
   <displacement unit="CC">580.7</displacement>
   <maxhp>65.00</maxhp>
   <cycles>4.0</cycles> <!-- tuned to gain 65hp -->
@@ -24,5 +24,8 @@
   <minthrottle>0.1</minthrottle>
   <bsfc>0.314</bsfc> <!-- tuned to gain 65hp -->
   <volumetric-efficiency>0.98</volumetric-efficiency>
+  <static-friction  unit="HP"> .5 </static-friction>
+  <man-press-lag> 0.1 </man-press-lag>
+
 </piston_engine>
 
diff --git a/Aircraft/c150/Engines/eng_O-200.xml b/Aircraft/c150/Engines/eng_O-200.xml
index 90e619c..81b4932 100644
--- a/Aircraft/c150/Engines/eng_O-200.xml
+++ b/Aircraft/c150/Engines/eng_O-200.xml
@@ -1,35 +1,34 @@
 <?xml version="1.0"?>
-<!--
-  File:     o-200.xml
-  Author:   Aero-Matic v 0.8
-
-  Inputs:
-    name:           o-200
-    type:           piston
-    power:          100.0 hp
-    augmented?      no
-    injected?       no
-
-O-200: 100 hp (75 kW)
-specifications
-
-4-cylinder, horizontally-opposed, air-cooled piston engine
-Displacement: 201 cubic inches  (3.3 litres)
-Bore x stroke: 4.0625 x 3.875 inches
-used by
-
-Aeronca 7EC Champion
-Cessna 150 
-
--->
-
+    <!--
+      File:     eng_O-200.xml
+      Author:   Ron Jensen
+     
+    O-200: 100 hp (75 kW)
+    specifications
+     
+    4-cylinder, horizontally-opposed, air-cooled piston engine
+    Displacement: 201 cubic inches  (3.3 litres)
+    Bore x stroke: 4.0625 x 3.875 inches
+    used by
+     
+    Aeronca 7EC Champion
+    Cessna 150
+     
+    Reference TCDS E-252
+    -->
+     
 <piston_engine name="o-200">
-  <minmp unit="INHG">          6.0 </minmp>
-  <maxmp unit="INHG">         30.0 </maxmp>
-  <displacement unit="IN3"> 201.00 </displacement>
-  <maxhp>        100.00 </maxhp>
-  <cycles>         2.0 </cycles>
-  <idlerpm>      550.0 </idlerpm>
-  <maxthrottle>    1.0 </maxthrottle>
-  <minthrottle>    0.1 </minthrottle>
-</piston_engine>
+      <minmp unit="INHG">         10.5 </minmp>
+      <maxmp unit="INHG">         28.5 </maxmp>
+      <displacement unit="IN3"> 201.00 </displacement>
+      <maxhp>        100.00 </maxhp>
+      <cycles>         4.0 </cycles>
+      <idlerpm>      550.0 </idlerpm>
+      <maxrpm>      2750.0 </maxrpm>
+      <bore unit="IN"> 4.0625 </bore>
+      <stroke unit="IN">3.875 </stroke>
+      <compression-ratio> 7.0 </compression-ratio>
+      <cylinders> 4 </cylinders>
+      <sparkfaildrop> 0.1 </sparkfaildrop>
+      <bsfc> 0.42 </bsfc>
+</piston_engine>
\ No newline at end of file
diff --git a/Aircraft/c150/Engines/prop_mccauley_6948.xml b/Aircraft/c150/Engines/prop_mccauley_6948.xml
index 899d6c0..6e5b741 100644
--- a/Aircraft/c150/Engines/prop_mccauley_6948.xml
+++ b/Aircraft/c150/Engines/prop_mccauley_6948.xml
@@ -1,115 +1,55 @@
 <?xml version="1.0"?>
-
+     
 <propeller name="Fixed-Pitch blabla-inch Two-Blade Propeller">
-  <ixx> 1.027 </ixx>
-  <!--
-  MoI ~ 0.5 * Prop_Weight(lb) (less hub) * [D2]/386
-  w=24lb
-  d=69inch=5.75ft
-  MoI ~ 1.027
-  -->
-  <!--ixx> 1.47452 </ixx-->
-  <diameter unit="IN"> 68.9 </diameter>
-  <numblades> 2 </numblades>
-  <minpitch> 30 </minpitch>
-  <maxpitch> 30 </maxpitch>
-  <gearratio>0.84 </gearratio>
-
-  <table name="C_THRUST" type="internal">
-     <tableData>
-       0.0  0.0197
-       0.1  0.0189
-       0.2  0.0181
-       0.3  0.0167
-       0.4  0.0150
-       0.5  0.0132
-       0.6  0.0107
-       0.7  0.0081
-       0.8  0.0044
-       1.0  -0.0015
-       1.2  -0.0078
-       1.4  -0.0140
-     </tableData>
-  </table>
-
-  <table name="C_POWER" type="internal">
-     <tableData>
-       0.0  0.0229
-       0.1  0.0229
-       0.2  0.0224
-       0.3  0.0219
-       0.4  0.0206
-       0.5  0.0189
-       0.6  0.0173
-       0.7  0.0145
-       0.8  0.0119
-       1.0  0.0042
-       1.2  -0.0068
-       1.4  -0.0204
-       1.6  -0.0347
-     </tableData>
-  </table>
-
-  <!--table name="C_THRUST" type="internal">
-    <tableData>
-      0.0   0.068
-      0.1   0.068
-      0.2   0.067
-      0.3   0.066
-      0.4   0.064
-      0.5   0.061
-      0.6   0.057
-      0.7   0.050
-      0.8   0.040
-      0.9   0.029
-      1.0   0.019
-      1.1   0.008
-      1.2   -0.001
-      1.3   -0.008
-      1.4   -0.019
-      1.5   -0.029
-      1.6   -0.040
-      1.7   -0.050
-      1.8   -0.057
-      1.9   -0.061
-      2.0   -0.064
-      2.1   -0.066
-      2.2   -0.067
-      2.3   -0.068
-      5.0   -0.068
-    </tableData>
-  </table-->
-
-  <!--table name="C_POWER" type = "internal">
-    <tableData>
-      0.0   0.0580
-      0.1   0.0620
-      0.2   0.0600
-      0.3   0.0580
-      0.4   0.0520
-      0.5   0.0450
-      0.6   0.0421
-      0.7   0.0389
-      0.8   0.0346
-      0.9   0.0280
-      1.0   0.0202
-      1.1   0.0111
-      1.2   0.0075
-      1.3   0.0111
-      1.4   0.0202
-      1.5   0.0280
-      1.6   0.0346
-      1.7   0.0389
-      1.8   0.0421
-      1.9   0.0436
-      2.0   0.0445
-      2.1   0.0445
-      2.2   0.0442
-      2.3   0.0431
-      2.4   0.0424
-      5.0   0.0413
-    </tableData>
-  </table-->
-
+      <ixx> 1.027 </ixx>
+      <!--
+      MoI ~ 0.5 * Prop_Weight(lb) (less hub) * [D2]/386
+      w=24lb
+      d=69inch=5.75ft
+      MoI ~ 1.027
+      -->
+      <diameter unit="IN"> 68.9 </diameter>
+      <numblades> 2 </numblades>
+      <minpitch> 30 </minpitch>
+      <maxpitch> 30 </maxpitch>
+      <gearratio> 1.00 </gearratio>
+      <ct_factor> 2.00 </ct_factor>
+      <cp_factor> 2.00 </cp_factor>
+     
+      <table name="C_THRUST" type="internal">
+         <tableData>
+           0.0  0.0197
+           0.1  0.0189
+           0.2  0.0181
+           0.3  0.0167
+           0.4  0.0150
+           0.5  0.0132
+           0.6  0.0107
+           0.7  0.0081
+           0.8  0.0044
+           1.0  -0.0015
+           1.2  -0.0173
+           1.4  -0.0140
+           1.6  -0.0202
+         </tableData>
+      </table>
+     
+      <table name="C_POWER" type="internal">
+         <tableData>
+           0.0  0.0229
+           0.1  0.0229
+           0.2  0.0224
+           0.3  0.0219
+           0.4  0.0206
+           0.5  0.0189
+           0.6  0.0173
+           0.7  0.0145
+           0.8  0.0119
+           1.0  -0.0042
+           1.2  -0.0186
+           1.4  -0.0408
+           1.6  -0.0694
+         </tableData>
+      </table>
+     
 </propeller>
-
diff --git a/Aircraft/c150/c150.xml b/Aircraft/c150/c150.xml
index 48cab8c..e87427c 100644
--- a/Aircraft/c150/c150.xml
+++ b/Aircraft/c150/c150.xml
@@ -469,7 +469,7 @@
                 <description>Drag_due_to_Elevator_Deflection</description>
                 <product>
                     <property>aero/qbar-psf</property>
-                    <property>metrics/Sw-sqft</property>
+                    <property>metrics/Sh-sqft</property>
                     <abs><property>fcs/elevator-pos-norm</property></abs>
                     <value>0.0300</value>
                 </product>
diff --git a/Aircraft/c172r/Engines/engIO360C.xml b/Aircraft/c172r/Engines/engIO360C.xml
index 676bdb5..433d59d 100644
--- a/Aircraft/c172r/Engines/engIO360C.xml
+++ b/Aircraft/c172r/Engines/engIO360C.xml
@@ -11,7 +11,7 @@
   minthrottle:   minimum throttle setting (as before)
 -->
 <piston_engine name="IO360C">
-  <minmp unit="INHG">         6.5  </minmp>	<!-- Deprecated -->
+  <minmp unit="INHG">        10.0 </minmp>
   <maxmp unit="INHG">        28.5 </maxmp>	
   <displacement unit="IN3"> 360.0  </displacement>
   <maxhp>                   180.0  </maxhp>	
diff --git a/Aircraft/c182/Engines/engIO540AB1A5.xml b/Aircraft/c182/Engines/engIO540AB1A5.xml
index 76f0986..f3354f8 100644
--- a/Aircraft/c182/Engines/engIO540AB1A5.xml
+++ b/Aircraft/c182/Engines/engIO540AB1A5.xml
@@ -12,7 +12,7 @@
 -->
 
 <piston_engine name="IO540AB1A5">
-  <minmp unit="INHG">          6.5 </minmp>	<!-- Deprecated -->
+  <minmp unit="INHG">         10.0 </minmp>
   <maxmp unit="INHG">         28.5 </maxmp>	
   <displacement unit="IN3">  540.0 </displacement>
   <maxhp>        230.0 </maxhp>
diff --git a/Aircraft/c182rg/c182rg.xml b/Aircraft/c182rg/c182rg.xml
index fc5efba..b95654b 100644
--- a/Aircraft/c182rg/c182rg.xml
+++ b/Aircraft/c182rg/c182rg.xml
@@ -6,7 +6,6 @@
 
     <fileheader>
         <author> Stuart Buchanan </author>
-        <author> Ron Jensen </author>
         <filecreationdate> 2002-01-01 </filecreationdate>
         <description> Cessna C-182RG </description>
     </fileheader>
diff --git a/Aircraft/c310/Engines/engIO470D.xml b/Aircraft/c310/Engines/engIO470D.xml
index a16e4a9..bc97274 100644
--- a/Aircraft/c310/Engines/engIO470D.xml
+++ b/Aircraft/c310/Engines/engIO470D.xml
@@ -12,8 +12,8 @@
 -->
 
 <piston_engine name="IO470D">
-  <minmp unit="INHG">          6.5 </minmp>	<!-- Deprecated -->
-  <maxmp unit="INHG">         28.5 </maxmp>	<!-- Deprecated -->
+  <minmp unit="INHG">          9.3 </minmp>
+  <maxmp unit="INHG">         28.5 </maxmp>
   <displacement unit="IN3">  470.0 </displacement>
   <maxhp>        260.00 </maxhp>
   <cycles>         4.0 </cycles>
diff --git a/Aircraft/c310u3a/Engines/engIO470D.xml b/Aircraft/c310u3a/Engines/engIO470D.xml
index a16e4a9..bc97274 100644
--- a/Aircraft/c310u3a/Engines/engIO470D.xml
+++ b/Aircraft/c310u3a/Engines/engIO470D.xml
@@ -12,8 +12,8 @@
 -->
 
 <piston_engine name="IO470D">
-  <minmp unit="INHG">          6.5 </minmp>	<!-- Deprecated -->
-  <maxmp unit="INHG">         28.5 </maxmp>	<!-- Deprecated -->
+  <minmp unit="INHG">          9.3 </minmp>
+  <maxmp unit="INHG">         28.5 </maxmp>
   <displacement unit="IN3">  470.0 </displacement>
   <maxhp>        260.00 </maxhp>
   <cycles>         4.0 </cycles>
diff --git a/Aircraft/dc2/Engines/R-1820-R52.xml b/Aircraft/dc2/Engines/R-1820-R52.xml
index b04f7c5..a8493ad 100644
--- a/Aircraft/dc2/Engines/R-1820-R52.xml
+++ b/Aircraft/dc2/Engines/R-1820-R52.xml
@@ -9,7 +9,7 @@
 -->
 
 <piston_engine name="R-1820-R52">
-  <minmp unit="INHG">          6.0 </minmp>
+  <minmp unit="INHG">          9.8 </minmp>
   <maxmp unit="INHG">         37.0 </maxmp>
   <displacement unit="IN3"> 1820.0 </displacement>
   <!-- Defining <bsfc> over-rides the bsfc value calculated from <maxhp> -->
diff --git a/Aircraft/flash2a/Engines/503.xml b/Aircraft/flash2a/Engines/503.xml
index 541fd88..0e37042 100644
--- a/Aircraft/flash2a/Engines/503.xml
+++ b/Aircraft/flash2a/Engines/503.xml
@@ -1,23 +1,28 @@
 <?xml version="1.0"?>
 <!--
   File:     503.xml
-  Author:   Aero-Matic v 0.8
+  Author:   Ron Jensen
 
   Inputs:
-    name:           503
+    name:           Rotax 503 UL
     type:           piston
-    power:          75 hp
-    augmented?      no
-    injected?       no
+    reference:      http://www.heavenboundaviation.com/andyrotax2.htm
 -->
 
 <piston_engine name="503">
-  <minmp unit="INHG">          2.0 </minmp>
-  <maxmp unit="INHG">         30.0 </maxmp>
-  <displacement unit="IN3"> 30.00 </displacement>
-  <maxhp>        75.00 </maxhp>
-  <cycles>         2.0 </cycles>
+  <minmp unit="INHG">         11.0 </minmp>
+  <maxmp unit="INHG">         28.0 </maxmp>
+  <displacement unit="IN3"> 30.31 </displacement>
+  <maxhp>        50.00 </maxhp>
+  <cycles>         4.0 </cycles> <!-- Really 2, but the 2 stroke model isn't good. -->
   <idlerpm>      700.0 </idlerpm>
+  <bore unit="IN"> 2.835 </bore>
+  <stroke unit="IN"> 2.40 </stroke>
+  <cylinders>        2.0 </cylinders>  
+  <maxrpm>      6800.00 </maxrpm> 
+  <static-friction  unit="HP"> .5 </static-friction>
+  <man-press-lag> 0.1 </man-press-lag>
+
   <maxthrottle>    1.0 </maxthrottle>
   <minthrottle>    0.1 </minthrottle>
-</piston_engine>
\ No newline at end of file
+</piston_engine>
diff --git a/Aircraft/flash2a/Engines/prop_ivoprop.xml b/Aircraft/flash2a/Engines/prop_ivoprop.xml
index 8342a5e..9e7d83c 100644
--- a/Aircraft/flash2a/Engines/prop_ivoprop.xml
+++ b/Aircraft/flash2a/Engines/prop_ivoprop.xml
@@ -1,60 +1,111 @@
 <?xml version="1.0"?>
-<!-- Generated by Aero-Matic v 0.8
+<!-- Generated by Aero-Matic v 1.1
 
      Inputs:
-                horsepower: 75.0
-                     pitch: fixed
-            max engine rpm: 6500
+                horsepower: 50.0
+                     pitch: variable
+            max engine rpm: 6800
         prop diameter (ft): 5.1666666666667
 
      Outputs:
-              max prop rpm:3631.55
-                gear ratio:   1.79
-                       Cp0:0.021249
-                       Ct0:0.018274
-       static thrust (lbs): 113.44
+              max prop rpm: 3631.55
+                gear ratio:    1.87
+                       Cp0: 0.014166
+                       Ct0: 0.033007
+       static thrust (lbs):  204.90
+
+     Modified: 
+                gear ratio:   2.58 TCDS BM-14 issue 9
 -->
 
 <propeller name="prop">
-  <ixx> 1.0708 </ixx>
-  <diameter unit="IN"> 62.0 </diameter>
+  <ixx>   1.29 </ixx>
+  <diameter unit="IN">  62.0 </diameter>
   <numblades> 2 </numblades>
-  <gearratio>1.79 </gearratio>
+  <gearratio>  2.58 </gearratio>
+  <p_factor>   4.90 </p_factor>
+  <minpitch> 22 </minpitch>
+  <maxpitch> 45 </maxpitch>
+  <constspeed> 0</constspeed>
+  <minrpm>   3087 </minrpm>
+  <maxrpm>   3632 </maxrpm>
 
+ <!-- thrust coefficient as a function of advance ratio and blade angle -->
   <table name="C_THRUST" type="internal">
-     <tableData>
-       0.0  0.0183
-       0.1  0.0175
-       0.2  0.0168
-       0.3  0.0154
-       0.4  0.0139
-       0.5  0.0122
-       0.6  0.0099
-       0.7  0.0075
-       0.8  0.0041
-       1.0  -0.0014
-       1.2  -0.0072
-       1.4  -0.0129
-     </tableData>
+      <tableData>
+                -10        0         15        25        35        45        55        65       90
+      -0.2      -0.0161    0.0091    0.0330    0.0404    0.0446    0.0470    0.0433    0.0371   0.0000
+       0.0      -0.0239    0.0000    0.0330    0.0404    0.0446    0.0475    0.0444    0.0371   0.0000
+       0.2      -0.0268   -0.0083    0.0285    0.0396    0.0439    0.0475    0.0444    0.0371   0.0000
+       0.4      -0.0268   -0.0192    0.0215    0.0392    0.0431    0.0470    0.0444    0.0371   0.0000
+       0.6      -0.0268   -0.0268    0.0114    0.0353    0.0413    0.0458    0.0437    0.0371   0.0000
+       0.8      -0.0268   -0.0268    0.0006    0.0264    0.0400    0.0442    0.0437    0.0371   0.0000
+       1.0      -0.0268   -0.0268   -0.0107    0.0161    0.0384    0.0419    0.0433    0.0371   0.0000
+       1.2      -0.0268   -0.0268   -0.0221    0.0050    0.0316    0.0404    0.0433    0.0371   0.0000
+       1.4      -0.0268   -0.0268   -0.0268   -0.0072    0.0227    0.0398    0.0425    0.0371   0.0000
+       1.6      -0.0268   -0.0268   -0.0268   -0.0184    0.0124    0.0384    0.0417    0.0371   0.0000
+       1.8      -0.0268   -0.0268   -0.0268   -0.0268    0.0021    0.0330    0.0404    0.0371   0.0000
+       2.0      -0.0268   -0.0268   -0.0268   -0.0268   -0.0083    0.0258    0.0403    0.0371   0.0000
+       2.2      -0.0268   -0.0268   -0.0268   -0.0268   -0.0186    0.0186    0.0396    0.0371   0.0000
+       2.4      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268    0.0099    0.0323    0.0371   0.0000
+       2.6      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268    0.0013    0.0205    0.0330   0.0000
+       2.8      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0074    0.0134    0.0268   0.0000
+       3.0      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0161    0.0070    0.0206   0.0000
+       3.2      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0248    0.0006    0.0145   0.0000
+       3.4      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0058    0.0083   0.0000
+       3.6      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0122    0.0021   0.0000
+       3.8      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0186   -0.0041   0.0000
+       4.0      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0250   -0.0103   0.0000
+       6.0      -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   -0.0268   0.0000
+      </tableData>
   </table>
 
-
+ <!-- power coefficient as a function of advance ratio and blade angle -->
   <table name="C_POWER" type="internal">
      <tableData>
-       0.0  0.0212
-       0.1  0.0212
-       0.2  0.0207
-       0.3  0.0203
-       0.4  0.0191
-       0.5  0.0175
-       0.6  0.0160
-       0.7  0.0135
-       0.8  0.0110
-       1.0  0.0039
-       1.2  -0.0063
-       1.4  -0.0189
-       1.6  -0.0321
+               -10        0        15        25        35        45        55        65       90
+      -0.2      0.0024   0.0047    0.0165    0.0375    0.0647    0.0921    0.1062    0.1176   0.1176
+       0.0      0.0094   0.0024    0.0142    0.0350    0.0619    0.0921    0.1067    0.1176   0.1176
+       0.2      0.0135   0.0038    0.0137    0.0326    0.0592    0.0921    0.1067    0.1176   0.1176
+       0.4      0.0181   0.0083    0.0118    0.0300    0.0562    0.0921    0.1067    0.1176   0.1176
+       0.6      0.0222   0.0125    0.0078    0.0279    0.0527    0.0902    0.1062    0.1176   0.1176
+       0.8      0.0262   0.0168    0.0024    0.0237    0.0496    0.0861    0.1062    0.1176   0.1176
+       1.0      0.0302   0.0208    0.0024    0.0166    0.0467    0.0817    0.1058    0.1176   0.1176
+       1.2      0.0343   0.0166   -0.0078    0.0064    0.0414    0.0783    0.1051    0.1176   0.1176
+       1.4      0.0382   0.0288   -0.0118   -0.0047    0.0319    0.0772    0.1038    0.1176   0.1176
+       1.6      0.0422   0.0329   -0.0137   -0.0142    0.0201    0.0751    0.1016    0.1133   0.1176
+       1.8      0.0463   0.0368   -0.0142   -0.0237    0.0059    0.0666    0.0985    0.1109   0.1176
+       2.0      0.0503   0.0408   -0.0181   -0.0330   -0.0071    0.0567    0.0938    0.1087   0.1176
+       2.2      0.0543   0.0449   -0.0222   -0.0425   -0.0212    0.0460    0.0909    0.1038   0.1176
+       2.4      0.0584   0.0489   -0.0262   -0.0520   -0.0354    0.0329    0.0883    0.1016   0.1176
+       2.6      0.0623   0.0528   -0.0302   -0.0613   -0.0449    0.0137    0.0861    0.0980   0.1176
+       2.8      0.0663   0.0569   -0.0343   -0.0708   -0.0538   -0.0047    0.0843    0.0968   0.1176
+       3.0      0.0704   0.0609   -0.0382   -0.0803   -0.0637   -0.0212    0.0815    0.0968   0.1176
+       3.2      0.0744   0.0649   -0.0422   -0.0897   -0.0732   -0.0378    0.0762    0.0945   0.1176
+       3.4      0.0783   0.0690   -0.0463   -0.0992   -0.0826   -0.0543    0.0591    0.0921   0.1176
+       3.6      0.0824   0.0730   -0.0503   -0.1087   -0.0921   -0.0708    0.0415    0.0897   0.1176
+       3.8      0.0864   0.0769   -0.0543   -0.1176   -0.1016   -0.0874    0.0231    0.0868   0.1176
+       4.0      0.0904   0.0810   -0.0584   -0.1176   -0.1176   -0.1038    0.0047    0.0803   0.1176
+       6.0      0.1176   0.1176   -0.1176   -0.1176   -0.1176   -0.1176   -0.1176   -0.0708   0.1176
      </tableData>
   </table>
 
-</propeller>
\ No newline at end of file
+<!-- 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>
+