diff --git a/aircraft/EasyStar/EasyStar-datcom-set.xml b/aircraft/EasyStar/EasyStar-datcom-set.xml
new file mode 100644
index 0000000000000000000000000000000000000000..32d5786963b136c4906138d591cc308362bb1aa0
--- /dev/null
+++ b/aircraft/EasyStar/EasyStar-datcom-set.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0"?>
+<PropertyList xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xsi:noNamespaceSchemaLocation="../../XMLSchemas/PropertyList.xsd">
+    <sim>
+        <author>James Goppert</author>
+		<description>Multiplex Easy Star (DATCOM)</description>
+        <aircraft-version>0.0.0</aircraft-version>
+        <status>early-production</status>
+        <startup>
+            <splash-title>Multiplex Easy Star</splash-title>
+        </startup>
+        <model>
+            <path>Aircraft/EasyStar/Models/EasyStar-model.xml</path>
+        </model>
+        <sound>
+            <path>Aircraft/EasyStar/EasyStar-sound.xml</path>
+        </sound>
+		<flight-model>jsb</flight-model>
+        <aero>EasyStar-datcom</aero>
+    </sim>
+</PropertyList>
diff --git a/aircraft/EasyStar/EasyStar-datcom.xml b/aircraft/EasyStar/EasyStar-datcom.xml
new file mode 100644
index 0000000000000000000000000000000000000000..3f91cb2a3b077f87c3d7b94c6fd26b46aea03468
--- /dev/null
+++ b/aircraft/EasyStar/EasyStar-datcom.xml
@@ -0,0 +1,1372 @@
+<?xml version="1.0"?>
+<!-- 
+    This is the JSBSim config file for a PA34-200T SenecaII.
+    The aerodynamics sections was generated by datcom using
+    as much real input as available.
+    
+    Changes from datcom.xml
+    
+    - function attribute NAME must be lowercase
+    - missing function Delta_lift_due_to_flap_deflection in axis LIFT
+    - missing function Lift_due_to_Elevator_Deflection in axis LIFT
+-->
+<?xml-stylesheet href="JSBSim.xsl" type="application/xml"?>
+<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
+    xsi:noNamespaceSchemaLocation="file:/home/torsten/FlightGear/Aircraft/SenecaII/JSBSim.xsd"
+    name="EasyStar-datcom" version="2.0" release="BETA">
+    
+    <fileheader>
+        <author>James Goppert</author>
+        <filecreationdate>2010-6-3</filecreationdate>
+        <description>Multiplex Easy Star (DATCOM)</description>
+        <reference title="Multiplex Easy Star (DATCOM)"/>
+    </fileheader>
+    
+    <!-- **********************************************************************
+        METRICS
+        ********************************************************************** -->
+	<metrics>
+      <wingarea unit="FT2">        2.2792  </wingarea>
+      <wingspan unit="FT">         4.5000  </wingspan>
+      <chord unit="FT">             .5606  </chord>
+      <htailarea unit="FT2">        .4457  </htailarea>
+      <htailarm unit="FT">          .4280  </htailarm>
+      <vtailarea unit="FT2">        .1606  </vtailarea>
+      <vtailarm unit="FT">          .7127  </vtailarm>
+	 <!-- 
+            the aerodynamic reference point, common point for 
+            aerodynamic forces (lift and drag) 
+        -->
+      <location name="AERORP" unit="IN">
+         <x>  4.0 </x>
+         <y>  0.0 </y>
+         <z>  0.0 </z>
+      </location>
+	 <!-- the eyepoint of the pilot (left or right eye?) -->
+      <location name="EYEPOINT" unit="IN">
+         <x>  0.0 </x>
+         <y>  0.0 </y>
+         <z>  0.0 </z>
+      </location>
+	<!-- the visual reference point of the 3d model -->
+      <location name="VRP" unit="IN">
+         <x>  0.0 </x>
+         <y>  0.0 </y>
+         <z>  0.0 </z>
+      </location>
+   </metrics>
+
+    <!-- **********************************************************************
+        MASS_BALANCE
+        ********************************************************************** -->
+    <mass_balance>
+		<ixx unit="SLUG*FT2"> .1 </ixx>
+        <iyy unit="SLUG*FT2"> .1 </iyy>
+        <izz unit="SLUG*FT2"> .1 </izz>
+		<ixz unit="SLUG*FT2"> 0 </ixz>
+        <emptywt unit="LBS"> 2.0 </emptywt>
+        <!-- the center of gravity -->
+        <location name="CG" unit="IN">
+            <x> 3.0 </x>
+            <y> 0.0 </y>
+            <z> 0.0 </z>
+        </location>
+        <!--<pointmass name="PAYLOAD">-->
+            <!--<weight unit="LBS"> 0.0 </weight>-->
+            <!--<location name="POINTMASS" unit="IN">-->
+                <!--<x> 39.3 </x>-->
+                <!--<y> 0 </y>-->
+                <!--<z> 35.3 </z>-->
+            <!--</location>-->
+        <!--</pointmass>-->
+    </mass_balance>
+    <!-- **********************************************************************
+        UNDERCARRIAGE
+        ********************************************************************** -->
+    <ground_reactions>
+		<contact type="STRUCTURE" name="TAIL_SKID">
+			<location unit="IN">
+				<x> 27.0 </x>
+				<y> 0 </y>
+				<z>-2.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="NOSE">
+			<location unit="IN">
+				<x> -5.0 </x>
+				<y> 0.0 </y>
+				<z> 0.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="BOTTOM_CANOPY">
+			<location unit="IN">
+				<x> 0.0 </x>
+				<y> 0.0 </y>
+				<z> -3.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+
+		<contact type="STRUCTURE" name="LEFT_WING">
+			<location unit="IN">
+				<x> -3.0 </x>
+				<y> -27.5 </y>
+				<z> 1.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="RIGHT_WING">
+			<location unit="IN">
+				<x> -3.0 </x>
+				<y> 27.5 </y>
+				<z> 1.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="VERTICAL_TAIL">
+			<location unit="IN">
+				<x> 27.0 </x>
+				<y> 0.0 </y>
+				<z> 6.5 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="CABIN_TOP">
+			<location unit="IN">
+				<x> 0.0 </x>
+				<y> 0.0 </y>
+				<z> 2.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+    </ground_reactions>
+    <!-- **********************************************************************
+        PROPULSION
+        ********************************************************************** -->
+    <propulsion>
+        <engine file="HB2815-2000">
+            <location unit="IN">
+                <x> 10.0 </x>
+                <y> 0 </y>
+                <z> 3.0 </z>
+            </location>
+            <orient unit="DEG">
+                <roll> 0.0 </roll>
+                <pitch> -5 </pitch>
+                <yaw> 0 </yaw>
+            </orient>
+			<feed>0</feed>
+			<thruster file="apc6x4">
+                <location unit="IN">
+                    <x> 10.0 </x>
+                    <y> 0 </y>
+                    <z> 3.0 </z>
+                </location>
+                <orient unit="DEG">
+                    <roll> 0.0 </roll>
+                    <pitch> -5.0 </pitch>
+                    <yaw> 0.0 </yaw>
+                </orient>
+                <p_factor>1.0</p_factor>
+            </thruster>
+        </engine>
+		<!--throws warning if tank not included, no real purpose-->
+		<tank type="FUEL">    <!-- Tank number 0 -->
+			<location unit="IN">
+				<x> 0.0 </x>
+				<y> 0.0 </y>
+				<z> 0.0 </z>
+			</location>
+			<capacity unit="LBS"> 0.0001 </capacity>
+			<contents unit="LBS"> 0 </contents>
+		</tank>
+    </propulsion>
+    <!-- **********************************************************************
+        FLIGHT CONTROLS
+        ********************************************************************** -->
+    <flight_control name="EasyStar">
+        <!--       
+            Elevator
+        -->
+        <channel name="Pitch">
+            <summer name="Pitch Trim Sum">
+                <input>fcs/elevator-cmd-norm</input>
+                <input>fcs/pitch-trim-cmd-norm</input>
+                <clipto>
+                    <min>-1</min>
+                    <max>1</max>
+                </clipto>
+                <output>fcs/elevator-pos-norm</output>
+            </summer>
+            <aerosurface_scale name="Elevator Control">
+                <input>fcs/pitch-trim-sum</input>
+                <gain>0.01745</gain>
+                <range>
+                    <min>-28</min>
+                    <max>23</max>
+                </range>
+                <output>fcs/elevator-pos-rad</output>
+            </aerosurface_scale>
+        </channel>
+ 		<!--
+            Rudder
+        -->
+        <channel name="Yaw">
+            <summer name="Yaw Trim Sum">
+                <input>fcs/rudder-cmd-norm</input>
+                <input>fcs/yaw-trim-cmd-norm</input>
+                <clipto>
+                    <min>-1</min>
+                    <max>1</max>
+                </clipto>
+            </summer>
+			<!--<pure_gain name="Aileron Crossfeed">-->
+                <!--<input>fcs/aileron-cmd-norm</input>-->
+				<!--<gain>-1</gain>-->
+				<!--<output>fcs/rudder-pos-norm</output>-->
+            <!--</pure_gain>-->
+			<summer name="Yaw Mix">
+                <input>fcs/yaw-trim-sum</input>
+				<!--<input>fcs/aileron-crossfeed</input>-->
+                <clipto>
+                    <min>-1</min>
+                    <max>1</max>
+                </clipto>
+            </summer>
+            <aerosurface_scale name="Rudder Control">
+                <input>fcs/yaw-mix</input>
+                <gain>0.01745</gain>
+                <range>
+                    <min>-27</min>
+                    <max>27</max>
+                </range>
+                <output>fcs/rudder-pos-rad</output>
+			</aerosurface_scale>
+		</channel>
+		<!--
+            Throttle (linear vs rpm approx.)
+        -->
+        <channel name="Throttle">
+			<fcs_function name="fcs/rpm-scaled-throttle">
+				<function>
+					<pow>
+						<property>fcs/throttle-cmd-norm</property>
+						<value>3</value>
+					</pow>
+				</function>
+			</fcs_function>
+            <aerosurface_scale name="Throttle Control">
+				<input>fcs/rpm-scaled-throttle</input>
+                <range>
+                    <min>-1</min>
+                    <max>1</max>
+                </range>
+                <output>fcs/throttle-pos-norm</output>
+			</aerosurface_scale>
+		</channel>
+
+    </flight_control>
+
+<!--
+
+
+  ****************** IMPORTANT NOTICES **********************
+
+   This is an alpha version release of the DATCOM+ program for
+   JSBSIM. Nothing, and I do mean NOTHING, as been checked to 
+   verify that the parameters, units, sign conventions, or    
+   basically anything else is correct. Your mileage may vary. 
+
+   ***********************************************************
+
+   This file was generated by the USAF Digital DATCOM program.
+   This file is considered an intermediary file in the 
+   DATCOM/JSBSim process. This file may be overwritten without
+   warning, so any changes that you make in here may be lost.
+
+   If you intend to use this file as it is and modify it, make
+   sure that you take the necessary precautions to prevent it 
+   from being overwritten, like renaming it.
+
+
+   ***********************************************************
+
+
+   DISCLAIMER REQUIRED BY HQ USAF FOR PUBLIC RELEASE APPROVAL
+
+   THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION
+   IS RELEASED "AS IS".  THE U.S. GOVERNMENT MAKES NO
+   WARRANTY OF ANY KIND, EXPRESS OR IMPLIED, CONCERNING
+   THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION,
+   INCLUDING, WITHOUT LIMITATION, ANY WARRANTIES OF
+   MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE.
+   IN NO EVENT WILL THE U.S. GOVERNMENT BE LIABLE FOR ANY
+   DAMAGES, INCLUDING LOST PROFITS, LOST SAVINGS OR OTHER
+   INCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING OUT OF THE 
+   USE, OR INABILITY TO USE, THIS SOFTWARE OR ANY
+   ACCOMPANYING DOCUMENTATION, EVEN IF INFORMED IN ADVANCE
+   OF THE POSSIBILITY OF SUCH DAMAGES.
+
+
+   ***********************************************************
+-->
+
+
+
+
+
+
+
+<!-- **********************************************************************
+        AERODYNAMICS
+     **********************************************************************
+-->
+
+
+   <aerodynamics>
+
+      <alphalimits unit="DEG">
+         <min>  -16.00    </min>
+         <max>   24.00    </max>
+      </alphalimits>
+
+
+
+
+      <!-- ************************* 
+                Sign Conventions    
+           ************************* 
+
+           Control displacements
+                Stick    FWD  + / Aft -
+                Stick    Left + / Right -
+                Wheel    CCW  + / CW -
+                Pedal    Left + / Right -
+                Elevator trim Nose Up + / Nose down -
+
+           Surfaces
+                Elevator  TED + / TEU -
+                R Ail     TED + / TEU -
+                L Ail     TED + / TEU -
+                Rudder    TEL + / TER -
+
+           F&M, Accel, Rates, Displacements
+                Pitch     Up  + / Down -
+                Roll      Rgt + / Left -
+                Yaw       Rgt + / Left -
+
+           Other
+                Alpha     Up  + / Down -
+                Beta Wind in right ear + / Wind in left ear -
+                Slip Ball right of center + / left of center -
+      -->
+
+
+
+
+      <!-- ************************************** 
+                ASSUMPTIONS AND LIMITATIONS
+
+           There is no interaction between deflected surfaces modeled
+           so there is no change in elevator effects with the flaps
+           deflected, for example.
+
+           Terms known to be missing from DATCOM:
+              Power effects
+              Ground effects
+              Cyr, CyDr, Cyda, ClDr, Cndr
+
+           **************************************
+      -->
+
+
+      <!--
+           The following ground effect tables are NOT generated
+           by DATCOM, but provide representative effects.
+           These terms are not currently used in this model.
+      -->
+
+
+      <function name="aero/function/ground-effect-factor-lift">
+         <description>Change in lift due to ground effect factor</description>
+         <product>
+            <table>
+               <independentVar lookup="row">aero/h_b-mac-ft</independentVar>
+               <tableData>
+                  0.0  1.203
+                  0.1  1.127
+                  0.15 1.090
+                  0.2  1.073
+                  0.3  1.046
+                  0.4  1.055
+                  0.5  1.019
+                  0.6  1.013
+                  0.7  1.008
+                  0.8  1.006
+                  0.9  1.003
+                  1.0  1.002
+                  1.1  1.0
+               </tableData>
+            </table>
+         </product>
+      </function>
+
+      <function name="aero/function/ground-effect-factor-drag">
+         <description>Change in drag due to ground effect</description>
+         <product>
+            <table>
+               <independentVar lookup="row">aero/h_b-mac-ft</independentVar>
+               <tableData>
+                  0.0  0.480
+                  0.1  0.515
+                  0.15 0.629
+                  0.2  0.709
+                  0.3  0.815
+                  0.4  0.882
+                  0.5  0.928
+                  0.6  0.962
+                  0.7  0.988
+                  0.8  1.0
+                  0.9  1.0
+                  1.0  1.0
+                  1.1  1.0
+               </tableData>
+            </table>
+         </product>
+      </function>
+
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="LIFT">
+
+
+         <function name="aero/coefficient/CLwbh">
+            <description>
+               Lift due to alpha
+               Increase in CL decreases Period and damping,Dutch Roll damping
+               CL is low for landing
+            </description>
+            <product>
+               <property>aero/function/ground-effect-factor-lift</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -1.216    
+                       -8.000        -.4490    
+                       -6.000        -.2713    
+                       -4.000        -.9559E-01
+                       -2.000         .7950E-01
+                         .000         .2620    
+                        2.000         .4513    
+                        4.000         .6466    
+                        8.000         1.053    
+                        9.000         1.157    
+                        10.00         1.248    
+                        12.00         1.403    
+                        14.00         1.529    
+                        16.00         1.620    
+                        18.00         1.660    
+                        19.00         1.659    
+                        20.00         1.545    
+                        21.00         1.332    
+                        22.00         1.097    
+                        24.00         .8071    
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CLq">
+            <description>
+               Basic Lift Coefficient due to pitch rate(per degree)
+            </description>
+            <product>
+               <property>velocities/q-aero-rad_sec</property>
+               <value>57.29577951</value>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/ci2vel</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00         .1523    
+                       -8.000         .1523    
+                       -6.000         .1523    
+                       -4.000         .1523    
+                       -2.000         .1523    
+                         .000         .1523    
+                        2.000         .1523    
+                        4.000         .1523    
+                        8.000         .1523    
+                        9.000         .1523    
+                        10.00         .1523    
+                        12.00         .1523    
+                        14.00         .1523    
+                        16.00         .1523    
+                        18.00         .1523    
+                        19.00         .1523    
+                        20.00         .1523    
+                        21.00         .1523    
+                        22.00         .1523    
+                        24.00         .1523    
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CLad">
+            <description>
+               Basic Lift Coefficient due to AOA rate(per degree)
+               Important contributor to Short-Period damping
+               For low Cla, aircraft must land at high alpha
+            </description>
+            <product>
+               <property>aero/alphadot-deg_sec</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/ci2vel</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00         .3510E-01
+                       -8.000         .3144E-01
+                       -6.000         .3313E-01
+                       -4.000         .3315E-01
+                       -2.000         .3284E-01
+                         .000         .3296E-01
+                        2.000         .3277E-01
+                        4.000         .3230E-01
+                        8.000         .2898E-01
+                        9.000         .2806E-01
+                        10.00         .2572E-01
+                        12.00         .1946E-01
+                        14.00         .1550E-01
+                        16.00         .1016E-01
+                        18.00        -.2053E-02
+                        19.00        -.1167E-01
+                        20.00        -.3353E-01
+                        21.00        -.5670E-01
+                        22.00        -.5279E-01
+                        24.00        -.3183E-01
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CLDe">
+            <description>
+               Lift Coefficient due to Elevator Deflection
+               Positive surface deflection is trailing edge down
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <table>
+                  <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
+                  <tableData>
+                       -20.00        -.6476E-01
+                       -15.00        -.5856E-01
+                       -10.00        -.4002E-01
+                       -5.000        -.2001E-01
+                         .000         .4002E-04
+                        5.000         .2001E-01
+                        10.00         .4002E-01
+                        13.00         .5157E-01
+                        16.00         .6162E-01
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="DRAG">
+
+
+         <function name="aero/coefficient/CD">
+            <description>
+               Basic Drag Coefficient
+               Sense: Always positive
+               Main contributor to Phugoid damping: Greater Cd, Better damping
+            </description>
+            <product>
+               <property>aero/function/ground-effect-factor-lift</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00         .1667    
+                       -8.000         .4475E-01
+                       -6.000         .3290E-01
+                       -4.000         .2639E-01
+                       -2.000         .2554E-01
+                         .000         .3065E-01
+                        2.000         .4245E-01
+                        4.000         .6156E-01
+                        8.000         .1232    
+                        9.000         .1436    
+                        10.00         .1636    
+                        12.00         .2014    
+                        14.00         .2355    
+                        16.00         .2637    
+                        18.00         .2813    
+                        19.00         .2851    
+                        20.00         .2611    
+                        21.00         .2185    
+                        22.00         .1816    
+                        24.00         .1539    
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CdDe">
+            <description>
+               Drag Coefficient due to Elevator Deflection
+               Positive surface deflection is trailing edge down
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <independentVar lookup="column">fcs/elevator-pos-deg</independentVar>
+                  <tableData>
+                                     -20.00        -15.00        -10.00        -5.000          .000         5.000         10.00         13.00         16.00    
+                       -16.00         .5945E-02     .5210E-02     .3237E-02     .1444E-02    -.2539E-05    -.1095E-02    -.1842E-02    -.2114E-02    -.2256E-02
+                       -8.000         .3346E-02     .2862E-02     .1633E-02     .6419E-03    -.9344E-06    -.2931E-03    -.2373E-03    -.4624E-04     .2148E-03
+                       -6.000         .2700E-02     .2278E-02     .1234E-02     .4425E-03    -.5355E-06    -.9363E-04     .1616E-03     .4677E-03     .8290E-03
+                       -4.000         .2027E-02     .1671E-02     .8186E-03     .2349E-03    -.1202E-06     .1140E-03     .5768E-03     .1003E-02     .1468E-02
+                       -2.000         .1338E-02     .1048E-02     .3930E-03     .2209E-04     .3054E-06     .3268E-03     .1002E-02     .1551E-02     .2124E-02
+                         .000         .6550E-03     .4315E-03    -.2832E-04    -.1886E-03     .7268E-06     .5375E-03     .1424E-02     .2094E-02     .2773E-02
+                        2.000        -.3080E-04    -.1879E-03    -.4516E-03    -.4002E-03     .1150E-05     .7491E-03     .1847E-02     .2640E-02     .3425E-02
+                        4.000        -.7194E-03    -.8099E-03    -.8767E-03    -.6128E-03     .1575E-05     .9616E-03     .2272E-02     .3187E-02     .4079E-02
+                        8.000        -.2133E-02    -.2087E-02    -.1749E-02    -.1049E-02     .2448E-05     .1398E-02     .3145E-02     .4312E-02     .5423E-02
+                        9.000        -.2513E-02    -.2429E-02    -.1984E-02    -.1166E-02     .2683E-05     .1515E-02     .3379E-02     .4614E-02     .5784E-02
+                        10.00        -.2896E-02    -.2776E-02    -.2220E-02    -.1285E-02     .2920E-05     .1633E-02     .3616E-02     .4919E-02     .6148E-02
+                        12.00        -.3763E-02    -.3559E-02    -.2755E-02    -.1552E-02     .3453E-05     .1901E-02     .4151E-02     .5608E-02     .6972E-02
+                        14.00        -.4698E-02    -.4403E-02    -.3333E-02    -.1841E-02     .4031E-05     .2190E-02     .4728E-02     .6352E-02     .7861E-02
+                        16.00        -.5692E-02    -.5301E-02    -.3946E-02    -.2148E-02     .4650E-05     .2496E-02     .5342E-02     .7143E-02     .8806E-02
+                        18.00        -.6799E-02    -.6301E-02    -.4629E-02    -.2489E-02     .5328E-05     .2838E-02     .6025E-02     .8023E-02     .9858E-02
+                        19.00        -.7457E-02    -.6895E-02    -.5036E-02    -.2692E-02     .5729E-05     .3041E-02     .6431E-02     .8547E-02     .1048E-01
+                        20.00        -.8200E-02    -.7566E-02    -.5494E-02    -.2921E-02     .6195E-05     .3270E-02     .6889E-02     .9137E-02     .1119E-01
+                        21.00        -.9209E-02    -.8478E-02    -.6117E-02    -.3233E-02     .6812E-05     .3582E-02     .7512E-02     .9940E-02     .1215E-01
+                        22.00        -.1032E-01    -.9484E-02    -.6805E-02    -.3577E-02     .7499E-05     .3926E-02     .8201E-02     .1083E-01     .1321E-01
+                        24.00        -.1205E-01    -.1104E-01    -.7870E-02    -.4109E-02     .8561E-05     .4458E-02     .9265E-02     .1220E-01     .1485E-01
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="SIDE">
+
+
+         <function name="aero/coefficient/Cyb">
+            <description>
+               Side Force coefficient due to Sideslip(per degree)
+                Contributes to damping of Dutch Roll mode
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/beta-deg</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.3898E-02
+                       -8.000        -.3898E-02
+                       -6.000        -.3898E-02
+                       -4.000        -.3898E-02
+                       -2.000        -.3898E-02
+                         .000        -.3898E-02
+                        2.000        -.3898E-02
+                        4.000        -.3898E-02
+                        8.000        -.3898E-02
+                        9.000        -.3898E-02
+                        10.00        -.3898E-02
+                        12.00        -.3898E-02
+                        14.00        -.3898E-02
+                        16.00        -.3898E-02
+                        18.00        -.3898E-02
+                        19.00        -.3898E-02
+                        20.00        -.3898E-02
+                        21.00        -.3898E-02
+                        22.00        -.3898E-02
+                        24.00        -.3898E-02
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cyp">
+            <description>
+               Side Force Coefficient due to Roll Rate(per degree)
+            </description>
+            <product>
+               <property>velocities/p-aero-rad_sec</property>
+               <value>57.29577951</value>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/bi2vel</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.6446E-03
+                       -8.000        -.1072E-02
+                       -6.000        -.1171E-02
+                       -4.000        -.1268E-02
+                       -2.000        -.1364E-02
+                         .000        -.1460E-02
+                        2.000        -.1555E-02
+                        4.000        -.1651E-02
+                        8.000        -.1855E-02
+                        9.000        -.1955E-02
+                        10.00        -.2099E-02
+                        12.00        -.2372E-02
+                        14.00        -.2653E-02
+                        16.00        -.3034E-02
+                        18.00        -.3638E-02
+                        19.00        -.1454E-01
+                        20.00        -.5140E-03
+                        21.00        -.1285E-02
+                        22.00        -.1322E-02
+                        24.00        -.1076E-02
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+
+         <!-- *************************
+              Not calculated by DATCOM+
+              *************************
+         -->
+
+         <function name="aero/coefficient/Cyr">
+            <description>
+               Side Force due to Yaw Rate(DATCOM does not calculate)
+               Effect is small
+            </description>
+            <product>
+               <property>velocities/r-aero-rad_sec</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/bi2vel</property>
+               <value>    .000    </value>
+            </product>
+         </function>
+
+
+         <!-- *************************
+              Not calculated by DATCOM+
+              *************************
+         -->
+
+         <function name="aero/coefficient/CyDr">
+            <description>
+               Side Force due to rudder(DATCOM does not calculate)
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>fcs/rudder-pos-deg</property>
+               <value>    .000    </value>
+            </product>
+         </function>
+
+
+         <!-- *************************
+              Not calculated by DATCOM+
+              *************************
+         -->
+
+         <function name="aero/coefficient/CyDa">
+            <description>
+               Side Force due to aileron(DATCOM does not calculate)
+               Usually neglected
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>fcs/left-aileron-pos-deg</property>
+               <value>    .000    </value>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="ROLL">
+
+
+         <function name="aero/coefficient/Clb">
+            <description>
+               Roll Moment coefficient due to Beta(per degree)
+               Decrease of Clb to small negative value improves Dutch Roll Damping
+               High Positive value leads to excessive spiral instability
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/beta-deg</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.1224E-02
+                       -8.000        -.1221E-02
+                       -6.000        -.1219E-02
+                       -4.000        -.1216E-02
+                       -2.000        -.1212E-02
+                         .000        -.1208E-02
+                        2.000        -.1206E-02
+                        4.000        -.1204E-02
+                        8.000        -.1203E-02
+                        9.000        -.1204E-02
+                        10.00        -.1202E-02
+                        12.00        -.1194E-02
+                        14.00        -.1181E-02
+                        16.00        -.1162E-02
+                        18.00        -.1134E-02
+                        19.00        -.1116E-02
+                        20.00        -.1082E-02
+                        21.00        -.1034E-02
+                        22.00        -.9825E-03
+                        24.00        -.9008E-03
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Clp">
+            <description>
+               Roll Moment coefficient due to roll rate(per degree)
+               Clp alone determines damping-in-roll characteristics
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/bi2vel</property>
+               <property>velocities/p-aero-rad_sec</property>
+			   <!--Manually increased roll damping, problem with datcom?-->
+			   <value>-0.5</value>
+               <!--<table>-->
+                  <!--<independentVar lookup="row">aero/alpha-deg</independentVar>-->
+                  <!--<tableData>-->
+                       <!---16.00        -.7650E-02-->
+                       <!---8.000        -.7063E-02-->
+                       <!---6.000        -.6859E-02-->
+                       <!---4.000        -.6653E-02-->
+                       <!---2.000        -.6738E-02-->
+                         <!--.000        -.7039E-02-->
+                        <!--2.000        -.7303E-02-->
+                        <!--4.000        -.7498E-02-->
+                        <!--8.000        -.7737E-02-->
+                        <!--9.000        -.7239E-02-->
+                        <!--10.00        -.6298E-02-->
+                        <!--12.00        -.4816E-02-->
+                        <!--14.00        -.3420E-02-->
+                        <!--16.00        -.1548E-02-->
+                        <!--18.00         .8581E-03-->
+                        <!--19.00         .5957E-02-->
+                        <!--20.00         .1465E-01-->
+                        <!--21.00         .1964E-01-->
+                        <!--22.00         .1776E-01-->
+                        <!--24.00         .7247E-02-->
+                  <!--</tableData>-->
+               <!--</table>-->
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Clr">
+            <description>
+               Roll Moment coefficient due to yaw rate(per degree)
+               Considerable effect on Spiral mode. Large 
+               positive values leads to strong sprial instability.
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/bi2vel</property>
+               <property>velocities/r-aero-rad_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.3497E-02
+                       -8.000        -.1073E-02
+                       -6.000        -.4976E-03
+                       -4.000         .5472E-04
+                       -2.000         .5948E-03
+                         .000         .1162E-02
+                        2.000         .1754E-02
+                        4.000         .2366E-02
+                        8.000         .3626E-02
+                        9.000         .3944E-02
+                        10.00         .4217E-02
+                        12.00         .4651E-02
+                        14.00         .4975E-02
+                        16.00         .5166E-02
+                        18.00         .5164E-02
+                        19.00         .5079E-02
+                        20.00         .4606E-02
+                        21.00         .3766E-02
+                        22.00         .2861E-02
+                        24.00         .1748E-02
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+
+         <!-- *************************
+              Not calculated by DATCOM+
+              *************************
+         -->
+
+         <function name="aero/coefficient/ClDr">
+            <description>
+               Roll moment due to rudder(DATCOM does not calculate)
+               Usually insignificant in dynamic stability considerations
+               but is used in autopilot work
+            </description>
+            <product>
+               <property>metrics/bw-ft</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>fcs/rudder-pos-deg</property>
+               <value>    .000    </value>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="PITCH">
+
+
+         <function name="aero/coefficient/Cm_basic">
+            <description>
+               Basic_Pitch_moment_coefficient
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/cbarw-ft</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00         .6261    
+                       -8.000         .2937    
+                       -6.000         .2325    
+                       -4.000         .1590    
+                       -2.000         .7771E-01
+                         .000        -.5162E-02
+                        2.000        -.9019E-01
+                        4.000        -.1784    
+                        8.000        -.3681    
+                        9.000        -.4190    
+                        10.00        -.4685    
+                        12.00        -.5701    
+                        14.00        -.6714    
+                        16.00        -.7712    
+                        18.00          .000    
+                        19.00          .000    
+                        20.00          .000    
+                        21.00          .000    
+                        22.00          .000    
+                        24.00          .000    
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cmq">
+            <description>
+               Pitch moment coefficient due to pitch rate(per degree)
+                Pitch Damping Derivative
+               Very important to Short Period damping of oscillations
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/cbarw-ft</property>
+               <property>aero/ci2vel</property>
+               <property>velocities/q-aero-rad_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.2485    
+                       -8.000        -.2485    
+                       -6.000        -.2485    
+                       -4.000        -.2485    
+                       -2.000        -.2485    
+                         .000        -.2485    
+                        2.000        -.2485    
+                        4.000        -.2485    
+                        8.000        -.2485    
+                        9.000        -.2485    
+                        10.00        -.2485    
+                        12.00        -.2485    
+                        14.00        -.2485    
+                        16.00        -.2485    
+                        18.00        -.2485    
+                        19.00        -.2485    
+                        20.00        -.2485    
+                        21.00        -.2485    
+                        22.00        -.2485    
+                        24.00        -.2485    
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cmadot">
+            <description>
+               Pitch moment coefficient due to AOA rate(per degree)
+               Negitive Cmad increase Short Period damping
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/cbarw-ft</property>
+               <property>aero/ci2vel</property>
+               <property>aero/alphadot-deg_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.1061    
+                       -8.000        -.9502E-01
+                       -6.000        -.1001    
+                       -4.000        -.1002    
+                       -2.000        -.9926E-01
+                         .000        -.9960E-01
+                        2.000        -.9904E-01
+                        4.000        -.9762E-01
+                        8.000        -.8757E-01
+                        9.000        -.8480E-01
+                        10.00        -.7772E-01
+                        12.00        -.5882E-01
+                        14.00        -.4683E-01
+                        16.00        -.3071E-01
+                        18.00         .6206E-02
+                        19.00         .3526E-01
+                        20.00         .1013    
+                        21.00         .1714    
+                        22.00         .1595    
+                        24.00         .9619E-01
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CmDe">
+            <description>
+               Pitch moment coefficient due to elevator deflection
+               Positive surface deflection is trailing edge down
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/cbarw-ft</property>
+               <table>
+                  <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
+                  <tableData>
+                       -20.00         .2086    
+                       -15.00         .1871    
+                       -10.00         .1282    
+                       -5.000         .6409E-01
+                         .000        -.1282E-03
+                        5.000        -.6409E-01
+                        10.00        -.1282    
+                        13.00        -.1648    
+                        16.00        -.1970    
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="YAW">
+
+
+         <function name="aero/coefficient/Cnb">
+            <description>
+               Yaw moment coefficient due to sideslip(per degree)
+               Determines Dutch Roll and Spiral characteristics
+               Prevents side-slip and yawing moments
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/beta-deg</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00         .6403E-03
+                       -8.000         .6403E-03
+                       -6.000         .6403E-03
+                       -4.000         .6403E-03
+                       -2.000         .6403E-03
+                         .000         .6403E-03
+                        2.000         .6403E-03
+                        4.000         .6403E-03
+                        8.000         .6403E-03
+                        9.000         .6403E-03
+                        10.00         .6403E-03
+                        12.00         .6403E-03
+                        14.00         .6403E-03
+                        16.00         .6403E-03
+                        18.00         .6403E-03
+                        19.00         .6403E-03
+                        20.00         .6403E-03
+                        21.00         .6403E-03
+                        22.00         .6403E-03
+                        24.00         .6403E-03
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cnp">
+            <description>
+               Yaw moment coefficient due to roll rate(per degree)
+               Reduces Dutch Roll damping
+               positive value desireable
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/bi2vel</property>
+               <property>velocities/p-aero-rad_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00         .2909E-03
+                       -8.000         .1580E-03
+                       -6.000         .1150E-03
+                       -4.000         .5960E-04
+                       -2.000         .8267E-06
+                         .000        -.4457E-04
+                        2.000        -.7403E-04
+                        4.000        -.9603E-04
+                        8.000        -.1448E-03
+                        9.000        -.2952E-03
+                        10.00        -.5744E-03
+                        12.00        -.1081E-02
+                        14.00        -.1590E-02
+                        16.00        -.2209E-02
+                        18.00        -.2839E-02
+                        19.00        -.1963E-02
+                        20.00        -.6663E-02
+                        21.00        -.6409E-02
+                        22.00        -.4810E-02
+                        24.00        -.2047E-02
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cnr">
+            <description>
+               Yaw Moment coefficient due to yaw rate(per degree)
+               Main contributor to damping of Dutch Roll
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/bi2vel</property>
+               <property>velocities/r-aero-rad_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.8275E-03
+                       -8.000        -.7745E-03
+                       -6.000        -.7758E-03
+                       -4.000        -.7821E-03
+                       -2.000        -.7927E-03
+                         .000        -.8079E-03
+                        2.000        -.8285E-03
+                        4.000        -.8551E-03
+                        8.000        -.9275E-03
+                        9.000        -.9496E-03
+                        10.00        -.9698E-03
+                        12.00        -.1004E-02
+                        14.00        -.1030E-02
+                        16.00        -.1043E-02
+                        18.00        -.1037E-02
+                        19.00        -.1026E-02
+                        20.00        -.9793E-03
+                        21.00        -.9093E-03
+                        22.00        -.8479E-03
+                        24.00        -.7868E-03
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+
+         <!-- ******************************************************
+              CnDr is not calculated by DATCOM+, but a default value
+              is supplied
+              ******************************************************-->
+
+         <function name="aero/coefficient/CnDr">
+            <description>
+               Yaw Coefficient due to rudder(DATCOM does not calculate)
+               High value for controllablity, low value
+               for good dynamic stability
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>fcs/rudder-pos-deg</property>
+               <value>  -.1047E-02</value>
+            </product>
+         </function>
+
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+      <function name="aero/elev_hinge_moment_ft_lbs">
+         <description>
+            Elevator hinge moment in ft-lbs
+            HM = q * S * Cbar * ( Ch0 + Cha*alpha + Chd*delta )
+            Positive causes trailing edge down movement
+            Ch0 is used to artifically trim HM to zero
+         </description>
+         <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+            <value>   .4492E-01</value>	<!-- surface area of elevator -->
+            <value>   .9414E-01</value>	<!-- MAC of elevator -->
+            <sum>
+ <!--
+               <property>aero/Ch0_elev</property>	
+ -->
+               <product>
+                  <property>aero/alpha-deg</property>
+                  <table>                            	<!-- Ch-alpha -->
+                     <independentVar lookup="row">
+                     aero/alpha-deg</independentVar>
+                     <tableData>
+                          -16.00    	   .2169E-02
+                          -8.000    	   .2169E-02
+                          -6.000    	   .2169E-02
+                          -4.000    	   .2169E-02
+                          -2.000    	   .2169E-02
+                            .000    	   .2169E-02
+                           2.000    	   .2169E-02
+                           4.000    	   .2169E-02
+                           8.000    	   .2169E-02
+                           9.000    	   .2169E-02
+                           10.00    	   .1730E-01
+                           12.00    	   .1723E-01
+                           14.00    	   .1723E-01
+                           16.00    	   .1723E-01
+                           18.00    	   .1723E-01
+                           19.00    	   .1723E-01
+                           20.00    	   .1723E-01
+                           21.00    	   .1723E-01
+                           22.00    	   .1724E-01
+                           24.00    	   .1723E-01
+                     </tableData>
+                  </table>
+               </product>
+               <product>
+                  <property>fcs/elevator-pos-deg</property>
+                  <table>                            	<!-- Ch-delta elevator -->
+                     <independentVar lookup="row">
+                     fcs/elevator-pos-deg</independentVar>
+                     <tableData>
+                          -20.00    	   .1730E-01
+                          -15.00    	   .1723E-01
+                          -10.00    	   .1723E-01
+                          -5.000    	   .1723E-01
+                            .000    	   .1723E-01
+                           5.000    	   .1723E-01
+                           10.00    	   .1723E-01
+                           13.00    	   .1723E-01
+                           16.00    	   .1724E-01
+                     </tableData>
+                  </table>
+               </product>
+            </sum>
+         </product>
+      </function>
+
+   </aerodynamics>
+</fdm_config>
diff --git a/aircraft/EasyStar/EasyStar-windtunnel-set.xml b/aircraft/EasyStar/EasyStar-windtunnel-set.xml
new file mode 100644
index 0000000000000000000000000000000000000000..2be996c8c5338f99d3d377e5263abb5121c97475
--- /dev/null
+++ b/aircraft/EasyStar/EasyStar-windtunnel-set.xml
@@ -0,0 +1,20 @@
+<?xml version="1.0"?>
+<PropertyList xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xsi:noNamespaceSchemaLocation="../../XMLSchemas/PropertyList.xsd">
+    <sim>
+        <author>James Goppert</author>
+		<description>Multiplex Easy Star (wind tunnel)</description>
+        <aircraft-version>0.0.0</aircraft-version>
+        <status>early-production</status>
+        <startup>
+            <splash-title>Multiplex Easy Star</splash-title>
+        </startup>
+        <model>
+            <path>Aircraft/EasyStar/Models/EasyStar-model.xml</path>
+        </model>
+        <sound>
+            <path>Aircraft/EasyStar/EasyStar-sound.xml</path>
+        </sound>
+		<flight-model>jsb</flight-model>
+        <aero>EasyStar-windtunnel</aero>
+    </sim>
+</PropertyList>
diff --git a/aircraft/EasyStar/EasyStar-windtunnel.xml b/aircraft/EasyStar/EasyStar-windtunnel.xml
new file mode 100644
index 0000000000000000000000000000000000000000..e4e281625d3d50c203b61696b2e9be394c277b6f
--- /dev/null
+++ b/aircraft/EasyStar/EasyStar-windtunnel.xml
@@ -0,0 +1,1366 @@
+<?xml version="1.0"?>
+<!-- 
+    This is the JSBSim config file for a PA34-200T SenecaII.
+    The aerodynamics sections was generated by datcom using
+    as much real input as available.
+    
+    Changes from datcom.xml
+    
+    - function attribute NAME must be lowercase
+    - missing function Delta_lift_due_to_flap_deflection in axis LIFT
+    - missing function Lift_due_to_Elevator_Deflection in axis LIFT
+-->
+<?xml-stylesheet href="JSBSim.xsl" type="application/xml"?>
+<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
+    xsi:noNamespaceSchemaLocation="file:/home/torsten/FlightGear/Aircraft/SenecaII/JSBSim.xsd"
+    name="EasyStar-windtunnel" version="2.0" release="BETA">
+    
+    <fileheader>
+        <author>James Goppert</author>
+        <filecreationdate>2010-6-3</filecreationdate>
+        <description>Multiplex Easy Star (wind tunnel)</description>
+        <reference title="Multiplex Easy Star (wind tunnel)"/>
+    </fileheader>
+    
+    <!-- **********************************************************************
+        METRICS
+        ********************************************************************** -->
+	<metrics>
+      <wingarea unit="FT2">        2.2792  </wingarea>
+      <wingspan unit="FT">         4.5000  </wingspan>
+      <chord unit="FT">             .5606  </chord>
+      <htailarea unit="FT2">        .4457  </htailarea>
+      <htailarm unit="FT">          .4280  </htailarm>
+      <vtailarea unit="FT2">        .1606  </vtailarea>
+      <vtailarm unit="FT">          .7127  </vtailarm>
+	 <!-- 
+            the aerodynamic reference point, common point for 
+            aerodynamic forces (lift and drag) 
+        -->
+      <location name="AERORP" unit="IN">
+         <x>  4.0 </x>
+         <y>  0.0 </y>
+         <z>  0.0 </z>
+      </location>
+	 <!-- the eyepoint of the pilot (left or right eye?) -->
+      <location name="EYEPOINT" unit="IN">
+         <x>  0.0 </x>
+         <y>  0.0 </y>
+         <z>  0.0 </z>
+      </location>
+	<!-- the visual reference point of the 3d model -->
+      <location name="VRP" unit="IN">
+         <x>  0.0 </x>
+         <y>  0.0 </y>
+         <z>  0.0 </z>
+      </location>
+   </metrics>
+
+    <!-- **********************************************************************
+        MASS_BALANCE
+        ********************************************************************** -->
+    <mass_balance>
+		<ixx unit="SLUG*FT2"> .1 </ixx>
+        <iyy unit="SLUG*FT2"> .1 </iyy>
+        <izz unit="SLUG*FT2"> .1 </izz>
+		<ixz unit="SLUG*FT2"> 0 </ixz>
+        <emptywt unit="LBS"> 2.0 </emptywt>
+        <!-- the center of gravity -->
+        <location name="CG" unit="IN">
+            <x> 3.0 </x>
+            <y> 0.0 </y>
+            <z> 0.0 </z>
+        </location>
+        <!--<pointmass name="PAYLOAD">-->
+            <!--<weight unit="LBS"> 0.0 </weight>-->
+            <!--<location name="POINTMASS" unit="IN">-->
+                <!--<x> 39.3 </x>-->
+                <!--<y> 0 </y>-->
+                <!--<z> 35.3 </z>-->
+            <!--</location>-->
+        <!--</pointmass>-->
+    </mass_balance>
+    <!-- **********************************************************************
+        UNDERCARRIAGE
+        ********************************************************************** -->
+    <ground_reactions>
+		<contact type="STRUCTURE" name="TAIL_SKID">
+			<location unit="IN">
+				<x> 27.0 </x>
+				<y> 0 </y>
+				<z>-2.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="NOSE">
+			<location unit="IN">
+				<x> -5.0 </x>
+				<y> 0.0 </y>
+				<z> 0.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="BOTTOM_CANOPY">
+			<location unit="IN">
+				<x> 0.0 </x>
+				<y> 0.0 </y>
+				<z> -3.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+
+		<contact type="STRUCTURE" name="LEFT_WING">
+			<location unit="IN">
+				<x> -3.0 </x>
+				<y> -27.5 </y>
+				<z> 1.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="RIGHT_WING">
+			<location unit="IN">
+				<x> -3.0 </x>
+				<y> 27.5 </y>
+				<z> 1.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="VERTICAL_TAIL">
+			<location unit="IN">
+				<x> 27.0 </x>
+				<y> 0.0 </y>
+				<z> 6.5 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+		<contact type="STRUCTURE" name="CABIN_TOP">
+			<location unit="IN">
+				<x> 0.0 </x>
+				<y> 0.0 </y>
+				<z> 2.0 </z>
+			</location>
+			<static_friction> 1.0 </static_friction>
+			<dynamic_friction> 0.8 </dynamic_friction>
+			<spring_coeff unit="LBS/FT"> 12 </spring_coeff>
+			<damping_coeff unit="LBS/FT/SEC"> 1 </damping_coeff>
+		</contact>
+    </ground_reactions>
+    <!-- **********************************************************************
+        PROPULSION
+        ********************************************************************** -->
+    <propulsion>
+        <engine file="HB2815-2000">
+            <location unit="IN">
+                <x> 10.0 </x>
+                <y> 0 </y>
+                <z> 3.0 </z>
+            </location>
+            <orient unit="DEG">
+                <roll> 0.0 </roll>
+                <pitch> -5 </pitch>
+                <yaw> 0 </yaw>
+            </orient>
+			<feed>0</feed>
+			<thruster file="apc6x4">
+                <location unit="IN">
+                    <x> 10.0 </x>
+                    <y> 0 </y>
+                    <z> 3.0 </z>
+                </location>
+                <orient unit="DEG">
+                    <roll> 0.0 </roll>
+                    <pitch> -5.0 </pitch>
+                    <yaw> 0.0 </yaw>
+                </orient>
+                <p_factor>1.0</p_factor>
+            </thruster>
+        </engine>
+		<!--throws warning if tank not included, no real purpose-->
+		<tank type="FUEL">    <!-- Tank number 0 -->
+			<location unit="IN">
+				<x> 0.0 </x>
+				<y> 0.0 </y>
+				<z> 0.0 </z>
+			</location>
+			<capacity unit="LBS"> 0.0001 </capacity>
+			<contents unit="LBS"> 0 </contents>
+		</tank>
+    </propulsion>
+    <!-- **********************************************************************
+        FLIGHT CONTROLS
+        ********************************************************************** -->
+    <flight_control name="EasyStar">
+        <!--       
+            Elevator
+        -->
+        <channel name="Pitch">
+            <summer name="Pitch Trim Sum">
+                <input>fcs/elevator-cmd-norm</input>
+                <input>fcs/pitch-trim-cmd-norm</input>
+                <clipto>
+                    <min>-1</min>
+                    <max>1</max>
+                </clipto>
+                <output>fcs/elevator-pos-norm</output>
+            </summer>
+            <aerosurface_scale name="Elevator Control">
+                <input>fcs/pitch-trim-sum</input>
+                <gain>0.01745</gain>
+                <range>
+                    <min>-28</min>
+                    <max>23</max>
+                </range>
+                <output>fcs/elevator-pos-rad</output>
+            </aerosurface_scale>
+        </channel>
+ 		<!--
+            Rudder
+        -->
+        <channel name="Yaw">
+            <summer name="Yaw Trim Sum">
+                <input>fcs/rudder-cmd-norm</input>
+                <input>fcs/yaw-trim-cmd-norm</input>
+                <clipto>
+                    <min>-1</min>
+                    <max>1</max>
+                </clipto>
+            </summer>
+			<!--<pure_gain name="Aileron Crossfeed">-->
+                <!--<input>fcs/aileron-cmd-norm</input>-->
+				<!--<gain>-1</gain>-->
+				<!--<output>fcs/rudder-pos-norm</output>-->
+            <!--</pure_gain>-->
+			<summer name="Yaw Mix">
+                <input>fcs/yaw-trim-sum</input>
+				<!--<input>fcs/aileron-crossfeed</input>-->
+                <clipto>
+                    <min>-1</min>
+                    <max>1</max>
+                </clipto>
+            </summer>
+            <aerosurface_scale name="Rudder Control">
+                <input>fcs/yaw-mix</input>
+                <gain>0.01745</gain>
+                <range>
+                    <min>-27</min>
+                    <max>27</max>
+                </range>
+                <output>fcs/rudder-pos-rad</output>
+			</aerosurface_scale>
+		</channel>
+		<!--
+            Throttle (linear vs rpm approx.)
+        -->
+        <channel name="Throttle">
+			<fcs_function name="fcs/rpm-scaled-throttle">
+				<function>
+					<pow>
+						<property>fcs/throttle-cmd-norm</property>
+						<value>3</value>
+					</pow>
+				</function>
+			</fcs_function>
+            <aerosurface_scale name="Throttle Control">
+				<input>fcs/rpm-scaled-throttle</input>
+                <range>
+                    <min>-1</min>
+                    <max>1</max>
+                </range>
+                <output>fcs/throttle-pos-norm</output>
+			</aerosurface_scale>
+		</channel>
+
+    </flight_control>
+
+<!--
+
+
+  ****************** IMPORTANT NOTICES **********************
+
+   This is an alpha version release of the DATCOM+ program for
+   JSBSIM. Nothing, and I do mean NOTHING, as been checked to 
+   verify that the parameters, units, sign conventions, or    
+   basically anything else is correct. Your mileage may vary. 
+
+   ***********************************************************
+
+   This file was generated by the USAF Digital DATCOM program.
+   This file is considered an intermediary file in the 
+   DATCOM/JSBSim process. This file may be overwritten without
+   warning, so any changes that you make in here may be lost.
+
+   If you intend to use this file as it is and modify it, make
+   sure that you take the necessary precautions to prevent it 
+   from being overwritten, like renaming it.
+
+
+   ***********************************************************
+
+
+   DISCLAIMER REQUIRED BY HQ USAF FOR PUBLIC RELEASE APPROVAL
+
+   THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION
+   IS RELEASED "AS IS".  THE U.S. GOVERNMENT MAKES NO
+   WARRANTY OF ANY KIND, EXPRESS OR IMPLIED, CONCERNING
+   THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION,
+   INCLUDING, WITHOUT LIMITATION, ANY WARRANTIES OF
+   MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE.
+   IN NO EVENT WILL THE U.S. GOVERNMENT BE LIABLE FOR ANY
+   DAMAGES, INCLUDING LOST PROFITS, LOST SAVINGS OR OTHER
+   INCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING OUT OF THE 
+   USE, OR INABILITY TO USE, THIS SOFTWARE OR ANY
+   ACCOMPANYING DOCUMENTATION, EVEN IF INFORMED IN ADVANCE
+   OF THE POSSIBILITY OF SUCH DAMAGES.
+
+
+   ***********************************************************
+-->
+
+
+
+
+
+
+
+<!-- **********************************************************************
+        AERODYNAMICS
+     **********************************************************************
+-->
+
+
+   <aerodynamics>
+
+      <alphalimits unit="DEG">
+         <min>  -16.00    </min>
+         <max>   24.00    </max>
+      </alphalimits>
+
+
+
+
+      <!-- ************************* 
+                Sign Conventions    
+           ************************* 
+
+           Control displacements
+                Stick    FWD  + / Aft -
+                Stick    Left + / Right -
+                Wheel    CCW  + / CW -
+                Pedal    Left + / Right -
+                Elevator trim Nose Up + / Nose down -
+
+           Surfaces
+                Elevator  TED + / TEU -
+                R Ail     TED + / TEU -
+                L Ail     TED + / TEU -
+                Rudder    TEL + / TER -
+
+           F&M, Accel, Rates, Displacements
+                Pitch     Up  + / Down -
+                Roll      Rgt + / Left -
+                Yaw       Rgt + / Left -
+
+           Other
+                Alpha     Up  + / Down -
+                Beta Wind in right ear + / Wind in left ear -
+                Slip Ball right of center + / left of center -
+      -->
+
+
+
+
+      <!-- ************************************** 
+                ASSUMPTIONS AND LIMITATIONS
+
+           There is no interaction between deflected surfaces modeled
+           so there is no change in elevator effects with the flaps
+           deflected, for example.
+
+           Terms known to be missing from DATCOM:
+              Power effects
+              Ground effects
+              Cyr, CyDr, Cyda, ClDr, Cndr
+
+           **************************************
+      -->
+
+
+      <!--
+           The following ground effect tables are NOT generated
+           by DATCOM, but provide representative effects.
+           These terms are not currently used in this model.
+      -->
+
+
+      <function name="aero/function/ground-effect-factor-lift">
+         <description>Change in lift due to ground effect factor</description>
+         <product>
+            <table>
+               <independentVar lookup="row">aero/h_b-mac-ft</independentVar>
+               <tableData>
+                  0.0  1.203
+                  0.1  1.127
+                  0.15 1.090
+                  0.2  1.073
+                  0.3  1.046
+                  0.4  1.055
+                  0.5  1.019
+                  0.6  1.013
+                  0.7  1.008
+                  0.8  1.006
+                  0.9  1.003
+                  1.0  1.002
+                  1.1  1.0
+               </tableData>
+            </table>
+         </product>
+      </function>
+
+      <function name="aero/function/ground-effect-factor-drag">
+         <description>Change in drag due to ground effect</description>
+         <product>
+            <table>
+               <independentVar lookup="row">aero/h_b-mac-ft</independentVar>
+               <tableData>
+                  0.0  0.480
+                  0.1  0.515
+                  0.15 0.629
+                  0.2  0.709
+                  0.3  0.815
+                  0.4  0.882
+                  0.5  0.928
+                  0.6  0.962
+                  0.7  0.988
+                  0.8  1.0
+                  0.9  1.0
+                  1.0  1.0
+                  1.1  1.0
+               </tableData>
+            </table>
+         </product>
+      </function>
+
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="LIFT">
+
+
+         <function name="aero/coefficient/CLwbh">
+            <description>
+               Lift due to alpha
+               Increase in CL decreases Period and damping,Dutch Roll damping
+               CL is low for landing
+            </description>
+            <product>
+               <property>aero/function/ground-effect-factor-lift</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+				  <tableData>
+					  -8.00        -0.06335
+					  -6.00         0.038907
+					  -4.00         0.206593
+					  -2.00         0.345895
+					   0.00         0.457604
+					   2.00 	    0.590396
+					   4.00         0.716654
+					   6.00         0.881424
+					   8.00         0.979728
+					   10.00        1.086794
+					   11.00        1.132822
+					   12.00        1.181349
+					   13.00        1.193517
+					   14.00        1.204571
+					   15.00        1.21972
+					   16.00        1.216158
+					   17.00        1.155675
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CLq">
+            <description>
+               Basic Lift Coefficient due to pitch rate(per degree)
+            </description>
+            <product>
+               <property>velocities/q-aero-rad_sec</property>
+               <value>57.29577951</value>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/ci2vel</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00         .1523    
+                       -8.000         .1523    
+                       -6.000         .1523    
+                       -4.000         .1523    
+                       -2.000         .1523    
+                         .000         .1523    
+                        2.000         .1523    
+                        4.000         .1523    
+                        8.000         .1523    
+                        9.000         .1523    
+                        10.00         .1523    
+                        12.00         .1523    
+                        14.00         .1523    
+                        16.00         .1523    
+                        18.00         .1523    
+                        19.00         .1523    
+                        20.00         .1523    
+                        21.00         .1523    
+                        22.00         .1523    
+                        24.00         .1523    
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CLad">
+            <description>
+               Basic Lift Coefficient due to AOA rate(per degree)
+               Important contributor to Short-Period damping
+               For low Cla, aircraft must land at high alpha
+            </description>
+            <product>
+               <property>aero/alphadot-deg_sec</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/ci2vel</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       <!---16.00         .3510E-01-->
+                       <!---8.000         .3144E-01-->
+                       <!---6.000         .3313E-01-->
+                       <!---4.000         .3315E-01-->
+                       <!---2.000         .3284E-01-->
+                         <!--.000         .3296E-01-->
+                        <!--2.000         .3277E-01-->
+                        <!--4.000         .3230E-01-->
+                        <!--8.000         .2898E-01-->
+                        <!--9.000         .2806E-01-->
+                        <!--10.00         .2572E-01-->
+                        <!--12.00         .1946E-01-->
+                        <!--14.00         .1550E-01-->
+                        <!--16.00         .1016E-01-->
+                        <!--18.00        -.2053E-02-->
+                        <!--19.00        -.1167E-01-->
+                        <!--20.00        -.3353E-01-->
+                        <!--21.00        -.5670E-01-->
+                        <!--22.00        -.5279E-01-->
+                        <!--24.00        -.3183E-01-->
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CLDe">
+            <description>
+               Lift Coefficient due to Elevator Deflection
+               Positive surface deflection is trailing edge down
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <table>
+                  <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
+                  <tableData>
+                       -20.00        -.6476E-01
+                       -15.00        -.5856E-01
+                       -10.00        -.4002E-01
+                       -5.000        -.2001E-01
+                         .000         .4002E-04
+                        5.000         .2001E-01
+                        10.00         .4002E-01
+                        13.00         .5157E-01
+                        16.00         .6162E-01
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="DRAG">
+
+
+         <function name="aero/coefficient/CD">
+            <description>
+               Basic Drag Coefficient
+               Sense: Always positive
+               Main contributor to Phugoid damping: Greater Cd, Better damping
+            </description>
+            <product>
+               <property>aero/function/ground-effect-factor-lift</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+   					  -8.00         0.054935
+					  -6.00         0.054319
+					  -4.00         0.049043
+					  -2.00         0.054276
+					   0.00         0.058332
+					   2.00 	    0.053311
+					   4.00         0.058928
+					   6.00         0.068195
+					   8.00         0.083696
+					   10.00        0.090816
+					   11.00        0.105498
+					   12.00        0.123163
+					   13.00        0.125782
+					   14.00        0.141154
+					   15.00        0.147641
+					   16.00        0.174355
+					   17.00        0.207037
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CdDe">
+            <description>
+               Drag Coefficient due to Elevator Deflection
+               Positive surface deflection is trailing edge down
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <independentVar lookup="column">fcs/elevator-pos-deg</independentVar>
+                  <tableData>
+                                     -20.00        -15.00        -10.00        -5.000          .000         5.000         10.00         13.00         16.00    
+                       -16.00         .5945E-02     .5210E-02     .3237E-02     .1444E-02    -.2539E-05    -.1095E-02    -.1842E-02    -.2114E-02    -.2256E-02
+                       -8.000         .3346E-02     .2862E-02     .1633E-02     .6419E-03    -.9344E-06    -.2931E-03    -.2373E-03    -.4624E-04     .2148E-03
+                       -6.000         .2700E-02     .2278E-02     .1234E-02     .4425E-03    -.5355E-06    -.9363E-04     .1616E-03     .4677E-03     .8290E-03
+                       -4.000         .2027E-02     .1671E-02     .8186E-03     .2349E-03    -.1202E-06     .1140E-03     .5768E-03     .1003E-02     .1468E-02
+                       -2.000         .1338E-02     .1048E-02     .3930E-03     .2209E-04     .3054E-06     .3268E-03     .1002E-02     .1551E-02     .2124E-02
+                         .000         .6550E-03     .4315E-03    -.2832E-04    -.1886E-03     .7268E-06     .5375E-03     .1424E-02     .2094E-02     .2773E-02
+                        2.000        -.3080E-04    -.1879E-03    -.4516E-03    -.4002E-03     .1150E-05     .7491E-03     .1847E-02     .2640E-02     .3425E-02
+                        4.000        -.7194E-03    -.8099E-03    -.8767E-03    -.6128E-03     .1575E-05     .9616E-03     .2272E-02     .3187E-02     .4079E-02
+                        8.000        -.2133E-02    -.2087E-02    -.1749E-02    -.1049E-02     .2448E-05     .1398E-02     .3145E-02     .4312E-02     .5423E-02
+                        9.000        -.2513E-02    -.2429E-02    -.1984E-02    -.1166E-02     .2683E-05     .1515E-02     .3379E-02     .4614E-02     .5784E-02
+                        10.00        -.2896E-02    -.2776E-02    -.2220E-02    -.1285E-02     .2920E-05     .1633E-02     .3616E-02     .4919E-02     .6148E-02
+                        12.00        -.3763E-02    -.3559E-02    -.2755E-02    -.1552E-02     .3453E-05     .1901E-02     .4151E-02     .5608E-02     .6972E-02
+                        14.00        -.4698E-02    -.4403E-02    -.3333E-02    -.1841E-02     .4031E-05     .2190E-02     .4728E-02     .6352E-02     .7861E-02
+                        16.00        -.5692E-02    -.5301E-02    -.3946E-02    -.2148E-02     .4650E-05     .2496E-02     .5342E-02     .7143E-02     .8806E-02
+                        18.00        -.6799E-02    -.6301E-02    -.4629E-02    -.2489E-02     .5328E-05     .2838E-02     .6025E-02     .8023E-02     .9858E-02
+                        19.00        -.7457E-02    -.6895E-02    -.5036E-02    -.2692E-02     .5729E-05     .3041E-02     .6431E-02     .8547E-02     .1048E-01
+                        20.00        -.8200E-02    -.7566E-02    -.5494E-02    -.2921E-02     .6195E-05     .3270E-02     .6889E-02     .9137E-02     .1119E-01
+                        21.00        -.9209E-02    -.8478E-02    -.6117E-02    -.3233E-02     .6812E-05     .3582E-02     .7512E-02     .9940E-02     .1215E-01
+                        22.00        -.1032E-01    -.9484E-02    -.6805E-02    -.3577E-02     .7499E-05     .3926E-02     .8201E-02     .1083E-01     .1321E-01
+                        24.00        -.1205E-01    -.1104E-01    -.7870E-02    -.4109E-02     .8561E-05     .4458E-02     .9265E-02     .1220E-01     .1485E-01
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="SIDE">
+
+
+         <function name="aero/coefficient/Cyb">
+            <description>
+               Side Force coefficient due to Sideslip(per degree)
+                Contributes to damping of Dutch Roll mode
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/beta-deg</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.3898E-02
+                       -8.000        -.3898E-02
+                       -6.000        -.3898E-02
+                       -4.000        -.3898E-02
+                       -2.000        -.3898E-02
+                         .000        -.3898E-02
+                        2.000        -.3898E-02
+                        4.000        -.3898E-02
+                        8.000        -.3898E-02
+                        9.000        -.3898E-02
+                        10.00        -.3898E-02
+                        12.00        -.3898E-02
+                        14.00        -.3898E-02
+                        16.00        -.3898E-02
+                        18.00        -.3898E-02
+                        19.00        -.3898E-02
+                        20.00        -.3898E-02
+                        21.00        -.3898E-02
+                        22.00        -.3898E-02
+                        24.00        -.3898E-02
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cyp">
+            <description>
+               Side Force Coefficient due to Roll Rate(per degree)
+            </description>
+            <product>
+               <property>velocities/p-aero-rad_sec</property>
+               <value>57.29577951</value>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/bi2vel</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.6446E-03
+                       -8.000        -.1072E-02
+                       -6.000        -.1171E-02
+                       -4.000        -.1268E-02
+                       -2.000        -.1364E-02
+                         .000        -.1460E-02
+                        2.000        -.1555E-02
+                        4.000        -.1651E-02
+                        8.000        -.1855E-02
+                        9.000        -.1955E-02
+                        10.00        -.2099E-02
+                        12.00        -.2372E-02
+                        14.00        -.2653E-02
+                        16.00        -.3034E-02
+                        18.00        -.3638E-02
+                        19.00        -.1454E-01
+                        20.00        -.5140E-03
+                        21.00        -.1285E-02
+                        22.00        -.1322E-02
+                        24.00        -.1076E-02
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+
+         <!-- *************************
+              Not calculated by DATCOM+
+              *************************
+         -->
+
+         <function name="aero/coefficient/Cyr">
+            <description>
+               Side Force due to Yaw Rate(DATCOM does not calculate)
+               Effect is small
+            </description>
+            <product>
+               <property>velocities/r-aero-rad_sec</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>aero/bi2vel</property>
+               <value>    .000    </value>
+            </product>
+         </function>
+
+
+         <!-- *************************
+              Not calculated by DATCOM+
+              *************************
+         -->
+
+         <function name="aero/coefficient/CyDr">
+            <description>
+               Side Force due to rudder(DATCOM does not calculate)
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>fcs/rudder-pos-deg</property>
+               <value>    .000    </value>
+            </product>
+         </function>
+
+
+         <!-- *************************
+              Not calculated by DATCOM+
+              *************************
+         -->
+
+         <function name="aero/coefficient/CyDa">
+            <description>
+               Side Force due to aileron(DATCOM does not calculate)
+               Usually neglected
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>fcs/left-aileron-pos-deg</property>
+               <value>    .000    </value>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="ROLL">
+
+
+         <function name="aero/coefficient/Clb">
+            <description>
+               Roll Moment coefficient due to Beta(per degree)
+               Decrease of Clb to small negative value improves Dutch Roll Damping
+               High Positive value leads to excessive spiral instability
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/beta-deg</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.1224E-02
+                       -8.000        -.1221E-02
+                       -6.000        -.1219E-02
+                       -4.000        -.1216E-02
+                       -2.000        -.1212E-02
+                         .000        -.1208E-02
+                        2.000        -.1206E-02
+                        4.000        -.1204E-02
+                        8.000        -.1203E-02
+                        9.000        -.1204E-02
+                        10.00        -.1202E-02
+                        12.00        -.1194E-02
+                        14.00        -.1181E-02
+                        16.00        -.1162E-02
+                        18.00        -.1134E-02
+                        19.00        -.1116E-02
+                        20.00        -.1082E-02
+                        21.00        -.1034E-02
+                        22.00        -.9825E-03
+                        24.00        -.9008E-03
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Clp">
+            <description>
+               Roll Moment coefficient due to roll rate(per degree)
+               Clp alone determines damping-in-roll characteristics
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/bi2vel</property>
+               <property>velocities/p-aero-rad_sec</property>
+			   <!--Manually increased roll damping, problem with datcom?-->
+			   <value>-0.5</value>
+               <!--<table>-->
+                  <!--<independentVar lookup="row">aero/alpha-deg</independentVar>-->
+                  <!--<tableData>-->
+                       <!---16.00        -.7650E-02-->
+                       <!---8.000        -.7063E-02-->
+                       <!---6.000        -.6859E-02-->
+                       <!---4.000        -.6653E-02-->
+                       <!---2.000        -.6738E-02-->
+                         <!--.000        -.7039E-02-->
+                        <!--2.000        -.7303E-02-->
+                        <!--4.000        -.7498E-02-->
+                        <!--8.000        -.7737E-02-->
+                        <!--9.000        -.7239E-02-->
+                        <!--10.00        -.6298E-02-->
+                        <!--12.00        -.4816E-02-->
+                        <!--14.00        -.3420E-02-->
+                        <!--16.00        -.1548E-02-->
+                        <!--18.00         .8581E-03-->
+                        <!--19.00         .5957E-02-->
+                        <!--20.00         .1465E-01-->
+                        <!--21.00         .1964E-01-->
+                        <!--22.00         .1776E-01-->
+                        <!--24.00         .7247E-02-->
+                  <!--</tableData>-->
+               <!--</table>-->
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Clr">
+            <description>
+               Roll Moment coefficient due to yaw rate(per degree)
+               Considerable effect on Spiral mode. Large 
+               positive values leads to strong sprial instability.
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/bi2vel</property>
+               <property>velocities/r-aero-rad_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.3497E-02
+                       -8.000        -.1073E-02
+                       -6.000        -.4976E-03
+                       -4.000         .5472E-04
+                       -2.000         .5948E-03
+                         .000         .1162E-02
+                        2.000         .1754E-02
+                        4.000         .2366E-02
+                        8.000         .3626E-02
+                        9.000         .3944E-02
+                        10.00         .4217E-02
+                        12.00         .4651E-02
+                        14.00         .4975E-02
+                        16.00         .5166E-02
+                        18.00         .5164E-02
+                        19.00         .5079E-02
+                        20.00         .4606E-02
+                        21.00         .3766E-02
+                        22.00         .2861E-02
+                        24.00         .1748E-02
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+
+         <!-- *************************
+              Not calculated by DATCOM+
+              *************************
+         -->
+
+         <function name="aero/coefficient/ClDr">
+            <description>
+               Roll moment due to rudder(DATCOM does not calculate)
+               Usually insignificant in dynamic stability considerations
+               but is used in autopilot work
+            </description>
+            <product>
+               <property>metrics/bw-ft</property>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>fcs/rudder-pos-deg</property>
+               <value>    .000    </value>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="PITCH">
+
+
+         <function name="aero/coefficient/Cm_basic">
+            <description>
+               Basic_Pitch_moment_coefficient
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/cbarw-ft</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+					-16.00         .6261   
+					-8.000         .2937   
+					-6.000         .2325   
+					-4.000         .1590   
+					-2.000         .7771E-01
+					.000        -.5162E-02
+					2.000        -.9019E-01
+					4.000        -.1784   
+					8.000        -.3681   
+					9.000        -.4190   
+					10.00        -.4685   
+					12.00        -.5701   
+					14.00        -.6714   
+					16.00        -.7712   
+					18.00          .000   
+					19.00          .000   
+					20.00          .000   
+					21.00          .000   
+					22.00          .000   
+					24.00          .000   
+			 </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cmq">
+            <description>
+               Pitch moment coefficient due to pitch rate(per degree)
+                Pitch Damping Derivative
+               Very important to Short Period damping of oscillations
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/cbarw-ft</property>
+               <property>aero/ci2vel</property>
+               <property>velocities/q-aero-rad_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.2485    
+                       -8.000        -.2485    
+                       -6.000        -.2485    
+                       -4.000        -.2485    
+                       -2.000        -.2485    
+                         .000        -.2485    
+                        2.000        -.2485    
+                        4.000        -.2485    
+                        8.000        -.2485    
+                        9.000        -.2485    
+                        10.00        -.2485    
+                        12.00        -.2485    
+                        14.00        -.2485    
+                        16.00        -.2485    
+                        18.00        -.2485    
+                        19.00        -.2485    
+                        20.00        -.2485    
+                        21.00        -.2485    
+                        22.00        -.2485    
+                        24.00        -.2485    
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cmadot">
+            <description>
+               Pitch moment coefficient due to AOA rate(per degree)
+               Negitive Cmad increase Short Period damping
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/cbarw-ft</property>
+               <property>aero/ci2vel</property>
+               <property>aero/alphadot-deg_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.1061    
+                       -8.000        -.9502E-01
+                       -6.000        -.1001    
+                       -4.000        -.1002    
+                       -2.000        -.9926E-01
+                         .000        -.9960E-01
+                        2.000        -.9904E-01
+                        4.000        -.9762E-01
+                        8.000        -.8757E-01
+                        9.000        -.8480E-01
+                        10.00        -.7772E-01
+                        12.00        -.5882E-01
+                        14.00        -.4683E-01
+                        16.00        -.3071E-01
+                        18.00         .6206E-02
+                        19.00         .3526E-01
+                        20.00         .1013    
+                        21.00         .1714    
+                        22.00         .1595    
+                        24.00         .9619E-01
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/CmDe">
+            <description>
+               Pitch moment coefficient due to elevator deflection
+               Positive surface deflection is trailing edge down
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/cbarw-ft</property>
+               <table>
+                  <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
+                  <tableData>
+                       -20.00         .2086    
+                       -15.00         .1871    
+                       -10.00         .1282    
+                       -5.000         .6409E-01
+                         .000        -.1282E-03
+                        5.000        -.6409E-01
+                        10.00        -.1282    
+                        13.00        -.1648    
+                        16.00        -.1970    
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+     <axis name="YAW">
+
+
+         <function name="aero/coefficient/Cnb">
+            <description>
+               Yaw moment coefficient due to sideslip(per degree)
+               Determines Dutch Roll and Spiral characteristics
+               Prevents side-slip and yawing moments
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/beta-deg</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00         .6403E-03
+                       -8.000         .6403E-03
+                       -6.000         .6403E-03
+                       -4.000         .6403E-03
+                       -2.000         .6403E-03
+                         .000         .6403E-03
+                        2.000         .6403E-03
+                        4.000         .6403E-03
+                        8.000         .6403E-03
+                        9.000         .6403E-03
+                        10.00         .6403E-03
+                        12.00         .6403E-03
+                        14.00         .6403E-03
+                        16.00         .6403E-03
+                        18.00         .6403E-03
+                        19.00         .6403E-03
+                        20.00         .6403E-03
+                        21.00         .6403E-03
+                        22.00         .6403E-03
+                        24.00         .6403E-03
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cnp">
+            <description>
+               Yaw moment coefficient due to roll rate(per degree)
+               Reduces Dutch Roll damping
+               positive value desireable
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/bi2vel</property>
+               <property>velocities/p-aero-rad_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00         .2909E-03
+                       -8.000         .1580E-03
+                       -6.000         .1150E-03
+                       -4.000         .5960E-04
+                       -2.000         .8267E-06
+                         .000        -.4457E-04
+                        2.000        -.7403E-04
+                        4.000        -.9603E-04
+                        8.000        -.1448E-03
+                        9.000        -.2952E-03
+                        10.00        -.5744E-03
+                        12.00        -.1081E-02
+                        14.00        -.1590E-02
+                        16.00        -.2209E-02
+                        18.00        -.2839E-02
+                        19.00        -.1963E-02
+                        20.00        -.6663E-02
+                        21.00        -.6409E-02
+                        22.00        -.4810E-02
+                        24.00        -.2047E-02
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+         <function name="aero/coefficient/Cnr">
+            <description>
+               Yaw Moment coefficient due to yaw rate(per degree)
+               Main contributor to damping of Dutch Roll
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>aero/bi2vel</property>
+               <property>velocities/r-aero-rad_sec</property>
+               <table>
+                  <independentVar lookup="row">aero/alpha-deg</independentVar>
+                  <tableData>
+                       -16.00        -.8275E-03
+                       -8.000        -.7745E-03
+                       -6.000        -.7758E-03
+                       -4.000        -.7821E-03
+                       -2.000        -.7927E-03
+                         .000        -.8079E-03
+                        2.000        -.8285E-03
+                        4.000        -.8551E-03
+                        8.000        -.9275E-03
+                        9.000        -.9496E-03
+                        10.00        -.9698E-03
+                        12.00        -.1004E-02
+                        14.00        -.1030E-02
+                        16.00        -.1043E-02
+                        18.00        -.1037E-02
+                        19.00        -.1026E-02
+                        20.00        -.9793E-03
+                        21.00        -.9093E-03
+                        22.00        -.8479E-03
+                        24.00        -.7868E-03
+                  </tableData>
+               </table>
+            </product>
+         </function>
+
+
+         <!-- ******************************************************
+              CnDr is not calculated by DATCOM+, but a default value
+              is supplied
+              ******************************************************-->
+
+         <function name="aero/coefficient/CnDr">
+            <description>
+               Yaw Coefficient due to rudder(DATCOM does not calculate)
+               High value for controllablity, low value
+               for good dynamic stability
+            </description>
+            <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+               <property>metrics/bw-ft</property>
+               <property>fcs/rudder-pos-deg</property>
+               <value>  -.1047E-02</value>
+            </product>
+         </function>
+
+
+     </axis>
+
+
+
+
+<!-- ********************************************************************** -->
+
+
+      <function name="aero/elev_hinge_moment_ft_lbs">
+         <description>
+            Elevator hinge moment in ft-lbs
+            HM = q * S * Cbar * ( Ch0 + Cha*alpha + Chd*delta )
+            Positive causes trailing edge down movement
+            Ch0 is used to artifically trim HM to zero
+         </description>
+         <product>
+               <property>aero/qbar-psf</property>
+               <property>metrics/Sw-sqft</property>
+            <value>   .4492E-01</value>	<!-- surface area of elevator -->
+            <value>   .9414E-01</value>	<!-- MAC of elevator -->
+            <sum>
+ <!--
+               <property>aero/Ch0_elev</property>	
+ -->
+               <product>
+                  <property>aero/alpha-deg</property>
+                  <table>                            	<!-- Ch-alpha -->
+                     <independentVar lookup="row">
+                     aero/alpha-deg</independentVar>
+                     <tableData>
+                          -16.00    	   .2169E-02
+                          -8.000    	   .2169E-02
+                          -6.000    	   .2169E-02
+                          -4.000    	   .2169E-02
+                          -2.000    	   .2169E-02
+                            .000    	   .2169E-02
+                           2.000    	   .2169E-02
+                           4.000    	   .2169E-02
+                           8.000    	   .2169E-02
+                           9.000    	   .2169E-02
+                           10.00    	   .1730E-01
+                           12.00    	   .1723E-01
+                           14.00    	   .1723E-01
+                           16.00    	   .1723E-01
+                           18.00    	   .1723E-01
+                           19.00    	   .1723E-01
+                           20.00    	   .1723E-01
+                           21.00    	   .1723E-01
+                           22.00    	   .1724E-01
+                           24.00    	   .1723E-01
+                     </tableData>
+                  </table>
+               </product>
+               <product>
+                  <property>fcs/elevator-pos-deg</property>
+                  <table>                            	<!-- Ch-delta elevator -->
+                     <independentVar lookup="row">
+                     fcs/elevator-pos-deg</independentVar>
+                     <tableData>
+                          -20.00    	   .1730E-01
+                          -15.00    	   .1723E-01
+                          -10.00    	   .1723E-01
+                          -5.000    	   .1723E-01
+                            .000    	   .1723E-01
+                           5.000    	   .1723E-01
+                           10.00    	   .1723E-01
+                           13.00    	   .1723E-01
+                           16.00    	   .1724E-01
+                     </tableData>
+                  </table>
+               </product>
+            </sum>
+         </product>
+      </function>
+
+   </aerodynamics>
+</fdm_config>
diff --git a/scicoslab/scripts/fgrun.sh b/scicoslab/scripts/fgrun.sh
index 992d8c0cfeae5a8cce38054b1388c8ce15e084b8..3f77e5f69aa3250d48be285126623a2c13d76f74 100755
--- a/scicoslab/scripts/fgrun.sh
+++ b/scicoslab/scripts/fgrun.sh
@@ -1,11 +1,14 @@
 #!/bin/bash
-#--native-ctrls=socket,out,119,,5501,udp \
-#--native-ctrls=socket,in,120,,5502,udp \
+#--disable-textures \
+if [ $# != 1 ]
+then
+	echo usage: $0 aircraft
+	exit
+fi
+aircraft=$1
 fgfs \
---fdm=external \
---aircraft=c172p \
+--aircraft=$aircraft \
 --geometry=400x300 \
---native-fdm=socket,in,120,,5500,udp \
 --vc=30 \
 --altitude=1000 \
 --heading=90 \
@@ -17,7 +20,6 @@ fgfs \
 --shading-flat \
 --notrim \
 --fog-disable \
---disable-textures \
 --disable-specular-highlight \
 --disable-skyblend \
 --disable-random-objects \
diff --git a/scicoslab/scripts/fgrunExt.sh b/scicoslab/scripts/fgrunExt.sh
new file mode 100755
index 0000000000000000000000000000000000000000..ed9bd8012acf9ff87ab04f83484b411fef26ee3b
--- /dev/null
+++ b/scicoslab/scripts/fgrunExt.sh
@@ -0,0 +1,33 @@
+#!/bin/bash
+#--native-ctrls=socket,out,119,,5501,udp \
+#--native-ctrls=socket,in,120,,5502,udp \
+#--disable-textures \
+if [ $# != 1 ]
+then
+	echo usage: $0 aircraft
+	exit
+fi
+aircraft=$1
+fgfs \
+--fdm=external \
+--aircraft=$aircraft \
+--geometry=400x300 \
+--native-fdm=socket,in,120,,5500,udp \
+--vc=30 \
+--altitude=1000 \
+--heading=90 \
+--roll=0 \
+--pitch=0 \
+--wind=0@0 \
+--turbulence=0.0 \
+--timeofday=noon \
+--shading-flat \
+--notrim \
+--fog-disable \
+--disable-specular-highlight \
+--disable-skyblend \
+--disable-random-objects \
+--disable-panel \
+--disable-horizon-effect \
+--disable-clouds \
+--disable-anti-alias-hud