CVS: data/Aircraft/BV-141 bv141-yasim.xml, 1.2, 1.3
Emmanuel Baranger <[email protected]> Sat, 3 Apr 2010 06:20:55 -0500
| Newsgroups | gmane.games.flightgear.cvc |
|---|---|
| Message-ID | <[email protected]> |
Update of /var/cvs/FlightGear-0.9/data/Aircraft/BV-141
In directory baron.flightgear.org:/tmp/cvs-serv5046
Modified Files:
bv141-yasim.xml
Log Message:
- little update on FDM (thanks to Melchior for the YASim_import script)
Index: bv141-yasim.xml
===================================================================
RCS file: /var/cvs/FlightGear-0.9/data/Aircraft/BV-141/bv141-yasim.xml,v
retrieving revision 1.2
retrieving revision 1.3
diff -u -r1.2 -r1.3
--- bv141-yasim.xml 15 Apr 2009 08:59:27 -0000 1.2
+++ bv141-yasim.xml 3 Apr 2010 11:02:06 -0000 1.3
@@ -1,7 +1,17 @@
<?xml version="1.0" encoding="UTF-8"?>
-<!-- Blohm & Voss BV 141
- 2009 - BARANGER Emmanuel
+<!-- Blohm & Voss BV 141 - 2010 Emmanuel BARANGER
+
+ Dewoitine
+
+ sources : http://en.wikipedia.org/wiki/Dewoitine_D.520
+
+ wingspan : 14.00 m ( 45 ft 9 in)
+ length : 14.00 m ( 45 ft 9 in)
+ height : 3.60 m ( 11 ft 9 in)
+ max speed : 535 km/h ( 289 kts)
+ empty weight : 4700 kg ( 10363 lb)
+ engine : BMW 801 radial piston (1560 hp)
-->
<airplane mass="10000">
@@ -25,18 +35,17 @@
<cockpit x="4.402" y="-1.615" z="0.525"/>
<!-- Cabine -->
- <fuselage ax="5.442" ay="-1.634" az="-0.168" bx="0.402" by="-1.634" bz="-0.530"
- width="1.323" taper="0.97" midpoint="0"/>
+ <fuselage ax="5.442" ay="-1.634" az="-0.168" bx="0.402" by="-1.634" bz="-0.530" width="1.323" taper="0.7" midpoint="0.5"/>
<!-- Moteur -->
- <fuselage ax="5.811" ay="0.552" az="-0.120" bx="-4.095" by="0.552" bz="0.287"
- width="1.149" taper="0.258" midpoint="0"/>
+ <fuselage ax="5.420" ay="0.552" az="-0.120" bx="-4.095" by="0.552" bz="0.287" width="1.149" taper="0.7" midpoint="0.2"/>
<wing x="2.814" y="0.0" z="-0.215"
chord="2.374"
length="7.473"
taper="0.676"
- camber="0.065">
+ camber="0.065"
+ dihedral="3">
<stall aoa="16" width="1.0" peak="1.5"/>
<flap0 start="0" end="0.58" lift="1.4" drag="1.5"/>
<flap1 start="0.58" end="0.98" lift="1.2" drag="1.1"/>
@@ -63,9 +72,9 @@
<vstab x="-3.617" y="0.546" z="-0.244"
chord="1.040"
- length="2.377"
- taper="0.96"
- sweep="26.6">
+ length="2.25"
+ taper="0.7"
+ sweep="0">
<stall aoa="14" width="3" peak="1.5"/>
<flap0 start="0" end="1" lift="1.5" drag="1.2"/>
<control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/>
@@ -73,21 +82,16 @@
<control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm" min="1" max="-1"/>
</vstab>
- <!-- Ref : "http://en.wikipedia.org/wiki/BMW_801"
+ <!-- Source : http://en.wikipedia.org/wiki/BMW_801"
- Engine : BMW 801
- weight : 2,325 lb (1,055 kg)
- Displacement : 2,547.4 in3 (41.8 l)
- Compression : 6.5:1
-
-
- Rayon * Rayon * Mass(kg) 1.5 * 1.5 * 1055
- moment d'après la doc : ________________________ = ____________________ = 791.25
- 3 3
+ Engine : BMW 801
+ weight : 2325 lb (1055 kg)
+ Displacement : 2547.4 in3 (41.8 l)
+ Compression : 6.5:1
-->
<propeller x="4.853" y="0.552" z="-0.120"
mass="1642"
- moment="791.25"
+ moment="35"
radius="1.5"
cruise-power="1065"
cruise-speed="240"
@@ -150,7 +154,7 @@
<tank x="4.5" y="4.0" z="-0.215" capacity="300"/>
<tank x="4.5" y="-4.0" z="-0.215" capacity="300"/>
- <!-- CG théiroque centre de la corde : x=2.814 y=0.000 z=-0.215 -->
+ <!-- CG theorique centre de la corde : x=2.814 y=0.000 z=-0.215 -->
<ballast x="9.5" y="0.685" z="-2.32" mass="1500"/>
</airplane>
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