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YASim: Difference between revisions
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Update for version 2018.1
(Update for version 2018.1) |
(Update for version 2018.1) |
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* <code>YASIM_VERSION_CURRENT</code> use latest version compiled into the users FlightGear. | * <code>YASIM_VERSION_CURRENT</code> use latest version compiled into the users FlightGear. | ||
{{Warning| Using YASIM_VERSION_CURRENT might make the aircraft unusable in case of future changes to YASim without updating the aircraft accordingly.}} | {{Warning| Using YASIM_VERSION_CURRENT might make the aircraft unusable in case of future changes to YASim without updating the aircraft accordingly.}} | ||
New in 2018.1 | |||
* '''mtow-lbs''' and '''mtow-kg:''' use (exactly) one of them to specify max. takeoff weight | |||
=== approach === | === approach === | ||
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Many airliners have wings with a geometry that is just a little more complex than what YASim supported initially (tapered wing with some angles like sweep, dihedral, ...), e.g. they have an inboard section and an outboard section that can be described with YASim wing syntax. You can use a wing + a mstab XML element to describe this geometry but it is easier if YASim can just append more wing sections by simply adding more wing XML elements. This is now (Version 2018.1) possible, yasim will simply append sections if it finds more than one wing or hstab in the XML. | Many airliners have wings with a geometry that is just a little more complex than what YASim supported initially (tapered wing with some angles like sweep, dihedral, ...), e.g. they have an inboard section and an outboard section that can be described with YASim wing syntax. You can use a wing + a mstab XML element to describe this geometry but it is easier if YASim can just append more wing sections by simply adding more wing XML elements. This is now (Version 2018.1) possible, yasim will simply append sections if it finds more than one wing or hstab in the XML. | ||
You should use <wing append="1" ... > for all but the first wing/hstab declaration. | You should use <wing append="1" ... > for all but the first wing/hstab declaration. | ||
{{ | {{Note| YASim will ignore the root point x,y,z, the chord length and the incidence attributes, if you add append="1" and calculate those from the previous wing section. }} | ||
MAC calculation works for the whole wing. | MAC calculation works for the whole wing. | ||
=== More information from CLI tools === | |||
You should configure the maximum take of weight (MTOW) in your XML file by adding either ''mtow-lbs'' or ''mtow-kg'' attribute to the airplane: | |||
<code> <airplane mass="7500" version="2018.1" mtow-lbs="12500"> </code> | |||
'''Example output''' | |||
<pre> | |||
yasim dhc6.xml | |||
========================== | |||
= YASim solution results = | |||
========================== | |||
Iterations: 1050 | |||
Drag Coefficient: 22.274 | |||
Lift Ratio: 73.247 | |||
Cruise AoA: -3.52 deg | |||
Tail Incidence: 5.19 deg | |||
Approach Elevator: -0.848 | |||
CG: x:0.439, y:0.000, z:0.012 | |||
Wing MAC: (x:1.00, y:5.29), length:2.0 | |||
hard limit CG-x: 4.468 m | |||
soft limit CG-x: 0.500 m | |||
CG-x: 0.439 m | |||
CG-x rel. MAC: 28% | |||
soft limit CG-x: 0.400 m | |||
hard limit CG-x: -1.000 m | |||
wing span: 19.58 m | |||
sweep lead. edge: 0.0 .. 0.0 deg | |||
wing area: 35.95 m² | |||
wing load empty: 94.63 kg/m² (Empty 3402 kg) | |||
wing load MTOW: 157.71 kg/m² (MTOW 5670 kg) | |||
tail span: 6.460 m | |||
tail area: 8.820 m² | |||
wing lever: 0.061 m | |||
tail lever: -7.559 m | |||
max thrust: 36.36 kN | |||
thrust/empty: 1.09 | |||
thrust/mtow: 0.65 | |||
Inertia tensor [kg*m^2], origo at CG: | |||
47625, -0, 15426 | |||
-0, 61844, 60 | |||
15426, 60, 91592 | |||
</pre> | |||
== Related content == | == Related content == | ||
* [[Howto:Make a helicopter#XML Elements]] – Rotor and rotorgear YASim elements | * [[Howto:Make a helicopter#XML Elements]] – Rotor and rotorgear YASim elements | ||