diff --git a/Engine/PW125B_sim.xml b/Engine/PW125B_sim.xml
new file mode 100644
index 000000000..12a93e9b8
--- /dev/null
+++ b/Engine/PW125B_sim.xml
@@ -0,0 +1,90 @@
+<?xml version="1.0"?>
+<!--
+  File:     PW125B.xml
+  Author:   Aero-Matic v 0.2
+
+  Inputs:
+    name:           PW125B
+    type:           turboprop
+    power:          2500 hp
+    augmented?      no
+    injected?       no
+-->
+
+<FG_SIMTURBINE NAME="PW125B">
+  MAXMILTHRUST 4175
+  BYPASSRATIO    0.0
+  TSFC           0.55
+  ATSFC          0.0
+  IDLEN1        30.0
+  IDLEN2        60.0
+  MAXN1        100.0
+  MAXN2        100.0
+  AUGMENTED      0
+  AUGMETHOD      1
+  INJECTED       0
+<TABLE NAME="IdleThrust" TYPE="TABLE">
+  Idle_power_thrust_factor
+  6
+  6
+  velocities/mach-norm
+  position/h-sl-ft
+  none
+              0   10000   20000   30000   40000   50000
+  0.0    0.0836  0.0528  0.0694  0.0899  0.1183  0.1467
+  0.2    0.0501  0.0335  0.0544  0.0797  0.1049  0.1342
+  0.4    0.0047  0.0020  0.0272  0.0595  0.0891  0.1203
+  0.6    0.0     0.0     0.0     0.0276  0.0718  0.1073
+  0.8    0.0     0.0     0.0     0.0     0.0474  0.0868
+  1.0    0.0     0.0     0.0     0.0     0.0     0.0552
+</TABLE>
+<TABLE NAME="MilThrust" TYPE="TABLE">
+  Military_power_thrust_factor
+  6
+  6
+  velocities/mach-norm
+  position/h-sl-ft
+  none
+              0   10000   20000   30000   40000   50000
+  0.0    1.0000  0.7400  0.5340  0.3720  0.2410  0.1490
+  0.2    0.7340  0.6970  0.5060  0.3550  0.2310  0.1430
+  0.4    0.6210  0.5920  0.4060  0.3570  0.2330  0.1450
+  0.6    0.3510  0.2710  0.2020  0.1780  0.1020  0.0640
+  0.8    0.0200  0.0200  0.0200  0.0200  0.0200  0.0200
+  1.0    0.0     0.0     0.0     0.0     0.0     0.0
+</TABLE>
+<TABLE NAME="AugThrust" TYPE="TABLE">
+  Augmented_thrust_factor
+  8
+  6
+  velocities/mach-norm
+  position/h-sl-ft
+  none
+              0   10000   20000   30000   40000   50000
+  0.0    1.4146  1.4146  1.4146  1.4146  1.4146  1.4146
+  0.2    1.4146  1.4146  1.4146  1.4146  1.4146  1.4146
+  0.4    1.4146  1.4146  1.4146  1.4146  1.4146  1.4146
+  0.6    1.4146  1.4146  1.4146  1.4146  1.4146  1.4146
+  0.8    1.4146  1.4146  1.4146  1.4146  1.4146  1.4146
+  1.0    1.4146  1.4146  1.4146  1.4146  1.4146  1.4146
+  1.2    1.4146  1.4146  1.4146  1.4146  1.4146  1.4146
+  1.4    1.4146  1.4146  1.4146  1.4146  1.4146  1.4146
+</TABLE>
+<TABLE NAME="WaterFactor" TYPE="TABLE">
+  Water_injection_factor
+  8
+  6
+  velocities/mach-norm
+  position/h-sl-ft
+  none
+              0   10000   20000   30000   40000   50000
+  0.0    1.2000  1.2000  1.2000  1.2000  1.2000  1.2000
+  0.2    1.2000  1.2000  1.2000  1.2000  1.2000  1.2000
+  0.4    1.2000  1.2000  1.2000  1.2000  1.2000  1.2000
+  0.6    1.2000  1.2000  1.2000  1.2000  1.2000  1.2000
+  0.8    1.2000  1.2000  1.2000  1.2000  1.2000  1.2000
+  1.0    1.2000  1.2000  1.2000  1.2000  1.2000  1.2000
+  1.2    1.2000  1.2000  1.2000  1.2000  1.2000  1.2000
+  1.4    1.2000  1.2000  1.2000  1.2000  1.2000  1.2000
+</TABLE>
+</FG_SIMTURBINE>
diff --git a/Engine/propDA-R352_6-123-F_2.xml b/Engine/propDA-R352_6-123-F_2.xml
new file mode 100644
index 000000000..5c310515d
--- /dev/null
+++ b/Engine/propDA-R352_6-123-F_2.xml
@@ -0,0 +1,46 @@
+<xml version="1.0"?>
+<!-- Generated by Aero-Matic v 0.3
+
+     Inputs:
+       horsepower:   2500
+       pitch:        variable
+
+     Outputs:
+       linear-blade-inches: 265
+-->
+
+<FG_PROPELLER NAME="prop">
+  IXX        3.7910590942383
+  DIAMETER   144
+  NUMBLADES  6
+  MINPITCH   10
+  MAXPITCH   30
+  MINRPM    700
+  MAXRPM   2700
+  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
+</FG_PROPELLER>