diff --git a/Engine/CFM56.xml b/Engine/CFM56.xml
new file mode 100644
index 000000000..56f2fd5c0
--- /dev/null
+++ b/Engine/CFM56.xml
@@ -0,0 +1,45 @@
+<?xml version="1.0"?>
+<!-- CFM56 turbofan engine model
+     Version 0.9, 31 Jan 2003, David Culp, davidculp2@attbi.com
+_______________________________________________________________
+-->
+<FG_TURBINE NAME="CFM56">
+<!-- max static thrust at S.L. (installed), lbs -->
+  MAXMILTHRUST 19000
+<!-- augmentation not installed -->
+  MAXAUGTHRUST 19000
+<!-- Idle Thrust -->
+  <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  0.1341
+    0.4    0.0047  0.0020  0.0272  0.0595  0.0891  0.1203
+    0.6   -0.0804 -0.0560 -0.0237  0.0276  0.0718  0.1073
+    0.8   -0.2129 -0.1498 -0.1025 -0.0195  0.0473  0.0868
+    1.0   -0.2839 -0.1104 -0.0469 -0.0270 -0.0158  0.0552
+  </TABLE>
+
+  <TABLE NAME="MilThrust" TYPE="TABLE">
+    Effects_of_altitude_and_mach_on_thrust
+    7
+    6
+    velocities/mach-norm
+    position/h-sl-ft
+    none
+               0    10000   20000     30000    40000    50000
+    0.0   1.0000   0.7216   0.4890   0.3115   0.1932   0.1104
+    0.2   1.0000   0.7216   0.4979   0.3186   0.1948   0.1104
+    0.4   0.9945   0.7344   0.5213   0.3383   0.2050   0.1230
+    0.6   0.9968   0.7759   0.5591   0.3675   0.2240   0.1309
+    0.8   0.9771   0.8025   0.6112   0.4196   0.2563   0.1522
+    0.9   0.9300   0.7900   0.6000   0.3900   0.2300   0.1300
+    1.0   0.5000   0.5000   0.4000   0.2000   0.1500   0.0900
+  </TABLE>
+
+</FG_TURBINE>
diff --git a/Engine/CFM56_nozzle.xml b/Engine/CFM56_nozzle.xml
new file mode 100644
index 000000000..e9486b434
--- /dev/null
+++ b/Engine/CFM56_nozzle.xml
@@ -0,0 +1,13 @@
+<?xml version="1.0"?>
+<FG_NOZZLE NAME="CFM56 Nozzle">
+  <!--
+    PE      = Nozzle exit pressure, psf.
+    EXPR    = Nozzle expansion ratio, Ae/At, sqft.
+    NZL_EFF = Nozzle efficiency, 0.0 - 1.0
+    DIAM    = Nozzle diameter, ft.
+  -->
+  EXPR    1.0
+  NZL_EFF 1.0
+  DIAM    3.0
+</FG_NOZZLE>
+
diff --git a/Engine/CFM56_sim.xml b/Engine/CFM56_sim.xml
new file mode 100644
index 000000000..6ec1db0fa
--- /dev/null
+++ b/Engine/CFM56_sim.xml
@@ -0,0 +1,107 @@
+<?xml version="1.0"?>
+
+<!-- CFM56 turbofan engine model
+     Version 1.0, 14 Mar 2003, David Culp, davidculp2@attbi.com
+-->
+
+<FG_SIMTURBINE NAME="CFM56">
+  <!--
+     MAXMILTHRUST  max static thrust at S.L. (installed), lbf
+     BYPASSRATIO   bypass ratio
+     TSFC          thrust-specific fuel consumption (lbm/hr/lbf)
+     ATSFC         augmented TSFC (lbm/hr/lbf)
+     IDLEN1        idle percent rpm of fan spool
+     IDLEN2        idle percent rpm of inner spool
+     MAXN1         N1 at 100% throttle
+     MAXN2         N2 at 100% throttle
+     AUGMENTED     =1 if augmentation installed, else =0
+     INJECTED      =1 if water injection installed, else =0  
+
+     TABLE(0)      idle thrust vs. altitude and mach
+     TABLE(1)      maximum un-augmented thrust vs. altitude and mach
+     TABLE(2)      augmented thrust multiplier vs. altitude and mach
+     TABLE(3)      water-injection multiplier vs. altitude and mach
+  -->
+
+  MAXMILTHRUST 20000
+  BYPASSRATIO  5.9
+  TSFC         0.657
+  ATSFC        0.0
+  IDLEN1       30.0
+  IDLEN2       60.0
+  MAXN1        100.0
+  MAXN2        100.0
+  AUGMENTED    0
+  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  0.1341
+    0.4    0.0047  0.0020  0.0272  0.0595  0.0891  0.1203
+    0.6   -0.0804 -0.0560 -0.0237  0.0276  0.0718  0.1073
+    0.8   -0.2129 -0.1498 -0.1025 -0.0195  0.0473  0.0868
+    1.0   -0.2839 -0.1104 -0.0469 -0.0270 -0.0158  0.0552
+  </TABLE>
+
+  <TABLE NAME="MilThrust" TYPE="TABLE">
+    Effects_of_altitude_and_mach_on_thrust
+    7
+    6
+    velocities/mach-norm
+    position/h-sl-ft
+    none
+               0    10000   20000     30000    40000    50000
+    0.0   1.0000   0.7216   0.4890   0.3115   0.1932   0.1104
+    0.2   1.0000   0.7216   0.4979   0.3186   0.1948   0.1104
+    0.4   0.9945   0.7344   0.5213   0.3383   0.2050   0.1230
+    0.6   0.9968   0.7759   0.5591   0.3675   0.2240   0.1309
+    0.8   0.9771   0.8025   0.6112   0.4196   0.2563   0.1522
+    0.9   0.9300   0.7900   0.6000   0.3900   0.2300   0.1300
+    1.0   0.5000   0.5000   0.4000   0.2000   0.1500   0.0900
+  </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/J85-GE-5.xml b/Engine/J85-GE-5.xml
new file mode 100644
index 000000000..5b3cd9554
--- /dev/null
+++ b/Engine/J85-GE-5.xml
@@ -0,0 +1,58 @@
+<?xml version="1.0"?>
+<!-- J85-GE-5 afterburning turbojet engine model -->
+<FG_TURBINE NAME="J85">
+  <!-- max static thrust at S.L. (installed), lbs -->
+  MAXMILTHRUST 2050
+  <!-- max augmented thrust at S.L. (installed), lbs -->
+  MAXAUGTHRUST 2900
+  <!-- Idle Thrust -->
+  <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  0.1341
+    0.4    0.0047  0.0020  0.0272  0.0595  0.0891  0.1203
+    0.6   -0.0804 -0.0560 -0.0237  0.0276  0.0718  0.1073
+    0.8   -0.2129 -0.1498 -0.1025 -0.0195  0.0473  0.0868
+    1.0   -0.2839 -0.1104 -0.0469 -0.0270 -0.0158  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   0.7216   0.4890   0.3115   0.1932   0.1104
+    0.2   1.0000   0.7216   0.4979   0.3186   0.1948   0.1104
+    0.4   0.9945   0.7344   0.5213   0.3383   0.2050   0.1230
+    0.6   0.9968   0.7759   0.5591   0.3675   0.2240   0.1309
+    0.8   0.9771   0.8025   0.6112   0.4196   0.2563   0.1522
+    1.0   0.9211   0.7767   0.6349   0.4811   0.2997   0.1822
+  </TABLE>
+
+  <TABLE NAME="AugThrust" TYPE="TABLE">
+    Augmented_thrust
+    8
+    6
+    velocities/mach-norm
+    position/h-sl-ft
+    none
+                0    10000   20000     30000    40000    50000
+    0.0    0.6924   0.5193   0.3739   0.2423   0.1385   0.0865
+    0.2    0.7415   0.5435   0.3886   0.2535   0.1535   0.0900
+    0.4    0.7858   0.5837   0.4241   0.2823   0.1731   0.0981
+    0.6    0.8392   0.6546   0.4764   0.3214   0.1973   0.1113
+    0.8    0.9025   0.7296   0.5530   0.3848   0.2375   0.1367
+    1.0    1.0000   0.8073   0.6335   0.4668   0.2992   0.1751
+    1.2    1.0000   0.9000   0.7000   0.5300   0.4000   0.0200
+    1.4    1.0000   0.9000   0.8000   0.6000   0.5000   0.0200
+  </TABLE>
+</FG_TURBINE>
diff --git a/Engine/J85-GE-5_sim.xml b/Engine/J85-GE-5_sim.xml
new file mode 100644
index 000000000..d2e2e1530
--- /dev/null
+++ b/Engine/J85-GE-5_sim.xml
@@ -0,0 +1,109 @@
+<?xml version="1.0"?>
+
+<!--
+  J85-GE-5 afterburning turbojet engine
+  for the JSBSim SimTurbine model
+-->
+
+<FG_SIMTURBINE NAME="J85">
+  <!--
+     MAXMILTHRUST  max static thrust at S.L. (installed), lbf
+     BYPASSRATIO   bypass ratio
+     TSFC          thrust-specific fuel consumption (lbm/hr/lbf)
+     ATSFC         augmented TSFC (lbm/hr/lbf)
+     IDLEN1        idle percent rpm of fan spool
+     IDLEN2        idle percent rpm of inner spool
+     MAXN1         N1 at 100% throttle
+     MAXN2         N2 at 100% throttle
+     AUGMENTED     =1 if augmentation installed
+     INJECTED      =1 if water injection installed  
+
+     TABLE(0)      idle thrust vs. altitude and mach
+     TABLE(1)      maximum un-augmented thrust vs. altitude and mach
+     TABLE(2)      augmented thrust multiplier vs. altitude and mach
+     TABLE(3)      water-injection multiplier vs. altitude and mach
+  -->
+
+  MAXMILTHRUST 2050
+  BYPASSRATIO  0
+  TSFC         1.1219
+  ATSFC        2.5172
+  IDLEN1       0.0
+  IDLEN2       49.2
+  MAXN1        0.0
+  MAXN2        100.0
+  AUGMENTED    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  0.1341
+    0.4    0.0047  0.0020  0.0272  0.0595  0.0891  0.1203
+    0.6   -0.0804 -0.0560 -0.0237  0.0276  0.0718  0.1073
+    0.8   -0.2129 -0.1498 -0.1025 -0.0195  0.0473  0.0868
+    1.0   -0.2839 -0.1104 -0.0469 -0.0270 -0.0158  0.0552
+  </TABLE>
+
+  <!-- data from EngineSim,  http://www.grc.nasa.gov/WWW/K-12/airplane/ngnsim.html -->
+  <TABLE NAME="MilThrust" TYPE="TABLE">
+    Military_power_thrust_factor
+    8
+    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   0.9340   0.6970   0.5060   0.3550   0.2310   0.1430
+    0.4   0.9210   0.6920   0.5060   0.3570   0.2330   0.1450
+    0.6   0.9510   0.7210   0.5320   0.3780   0.2480   0.1540
+    0.8   1.0200   0.7820   0.5820   0.4170   0.2750   0.1700
+    1.0   1.1200   0.8710   0.6510   0.4750   0.3150   0.1950
+    1.2   1.2300   0.9750   0.7440   0.5450   0.3640   0.2250
+    1.4   1.3400   1.0860   0.8450   0.6280   0.4240   0.2630
+  </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/J85_nozzle.xml b/Engine/J85_nozzle.xml
new file mode 100644
index 000000000..5568c0f87
--- /dev/null
+++ b/Engine/J85_nozzle.xml
@@ -0,0 +1,13 @@
+<?xml version="1.0"?>
+<FG_NOZZLE NAME="T38 Nozzle">
+  <!--
+    PE      = Nozzle exit pressure, psf.
+    EXPR    = Nozzle expansion ratio, Ae/At, sqft.
+    NZL_EFF = Nozzle efficiency, 0.0 - 1.0
+    DIAM    = Nozzle diameter, ft.
+  -->
+  EXPR    1.0
+  NZL_EFF 1.0
+  DIAM    2.0
+</FG_NOZZLE>
+