Difference between revisions of "YASim"

From FlightGear wiki
Jump to: navigation, search
(Export of YASim internals to property tree)
m (fuselage: them -> the)
Line 46: Line 46:
* '''midpoint:''' The location of the widest part of the fuselage, expressed as a fraction of the distance between A and B.
* '''midpoint:''' The location of the widest part of the fuselage, expressed as a fraction of the distance between A and B.
* '''idrag:''' Multiplier for the "induced drag" generated by this object. Default is one. With idrag=0 the fuselage generates only drag.
* '''idrag:''' Multiplier for the "induced drag" generated by this object. Default is one. With idrag=0 the fuselage generates only drag.
* '''cx,cy,cz:''' Factors for the generated drag in the fuselages "local coordinate system" with x pointing from end to front, z perpendicular to x with y=0 in the aircraft coordinate system. E.g. for a fuselage of a height of 2 times them width you can define cy=2 and (due to the doubled front surface) cx=2.
* '''cx,cy,cz:''' Factors for the generated drag in the fuselages "local coordinate system" with x pointing from end to front, z perpendicular to x with y=0 in the aircraft coordinate system. E.g. for a fuselage of a height of 2 times the width you can define cy=2 and (due to the doubled front surface) cx=2.
=== Surfaces ===
=== Surfaces ===

Revision as of 17:05, 2 September 2017

YASim is one of two flight dynamics models commonly used in FlightGear. The flight dynamics model (FDM) determines how the aircraft moves and flies.

Gary Neely wrote in his introduction to YASim:

The FDM is the mathematical model that controls the physics of flight within the simulator. The physical 3D aircraft model has nothing to do with flight dynamics-- in essence it's just a picture to look at. It's the FDM that dictates how the model flies.
Why YASim? YASim uses the geometry of the aircraft to generate the base flight characteristics. While this suggests a 'realistic' or out-of-the-box approach, it is a only rough approximation that will require much tweaking before you get a result that approaches realism. If you have solid flight data for your aircraft such as wind-tunnel data or you are looking to eventually generate a hyper-realistic simulation, JSBSim is probably a better approach. If you lack such data but know the geometry of the aircraft and have access to the same flight characteristics and limits as a real pilot would, then YASim can provide a solution that is more than sufficient for most simulation needs.

Coordinate system notes

All positions specified are in metres (which is weird, since all other units in the file are English). The X axis points forward, Y is left, and Z is up. Take your right hand, and hold it like a gun. Your first and second fingers are the X and Y axes, and your upwards-pointing thumb is the Z. This is slightly different from the coordinate system used by JSBSim. Sorry. The origin can be placed anywhere, so long as you are consistent. I use the nose of the aircraft.

(In the JSBSim coordinate system, X and Z are the same as in YASim, but Y points to the right instead of left.)

XML Elements


The top-level element for the file. It contains the following attributes:

  • mass: The empty (no fuel) weight, in pounds. It does include the weight of the engine(s), so when you add the engine weight in its tag, it acts just like a ballast.
  • version: The version attribute is used to maintain compatibility when updating yasim (e.g. bugfixes). If this attribute i not given, the original version will be used. Several bugfixes to YASim were implemented in FlightGear 3.2 (see FlightGear Newsletter April 2014), some more are fixed in FlightGear 2017.2.

Available versions are:

  • YASIM_VERSION_ORIGINAL explicitly use the old buggy calculations (same as no version attribute at all)
  • YASIM_VERSION_32 enable bugfixes up to version 3.2
  • 2017.2 enable bugfixes up to version 2017.2
  • YASIM_VERSION_CURRENT use latest version compiled into the users FlightGear. This might be dangerous in case of future changes.


The approach parameters for the aircraft. The solver will generate an aircraft that matches these settings. The element can (and should) contain <control> elements indicating pilot input settings, such as flaps and throttle, for the approach.

  • speed: The approach airspeed, in knots TAS.
  • aoa: The approach angle of attack, in degrees
  • fuel: Fraction (0-1) of fuel in the tanks. Default is 0.2.


The cruise speed and altitude for the solver to match. As above, this should contain <control> elements indicating aircraft configuration. Especially, make sure the engines are generating enough thrust at cruise!

  • speed: The cruise speed, in knots TAS.
  • alt: The cruise altitude, in feet MSL.
  • fuel: Fraction (0-1) of fuel in the tanks. Default is 0.2.


The location of the cockpit (pilot eyepoint).

  • x,y,z: eyepoint location (see coordinates note)


This defines a tubelike structure. It will be given an even mass and aerodynamic force distribution by the solver. You can have as many as you like, in any orientation you please.

  • ax,ay,az: One end of the tube (typically the front)
  • bx,by,bz: The other ("back") end.
  • width: The width of the tube, in metres.
  • taper: The approximate radius at the "tips" of the fuselage expressed as a fraction (0-1) of the width value.
  • midpoint: The location of the widest part of the fuselage, expressed as a fraction of the distance between A and B.
  • idrag: Multiplier for the "induced drag" generated by this object. Default is one. With idrag=0 the fuselage generates only drag.
  • cx,cy,cz: Factors for the generated drag in the fuselages "local coordinate system" with x pointing from end to front, z perpendicular to x with y=0 in the aircraft coordinate system. E.g. for a fuselage of a height of 2 times the width you can define cy=2 and (due to the doubled front surface) cx=2.



This defines the main wing of the aircraft. You can have only one (but see below about using vstab objects for extra lifting surfaces). The wing should have a <stall> subelement to indicate stall behavior, control surface subelements (flap0, flap1, spoiler, slat) to indicate what and where the control surfaces are, and <control> subelements to map user input properties to the control surfaces.

  • x,y,z: The "base" of the wing, specified as the location of the mid-chord (not leading edge, trailing edge, or aerodynamic center) point at the root of the LEFT (!) wing.
  • length: The length from the base of the wing to the midchord point at the tip. Note that this is not the same thing as span.
  • chord: The chord of the wing at its base, along the X axis (not normal to the leading edge, as it is sometimes defined).
  • incidence: The incidence angle at the wing root, in degrees. Zero is level with the fuselage (as in an aerobatic plane), positive means that the leading edge is higher than the trailing edge (as in a trainer).
  • twist: The difference between the incidence angle at the wing root and the incidence angle at the wing tip. Typically, this is a negative number so that the wing tips have a lower angle of attack and stall after the wing root (washout).
  • taper: The taper fraction, expressed as the tip chord divided by the root chord. A taper of one is a hershey bar wing, and zero would be a wing ending at a point. Defaults to one.
  • sweep: The sweep angle of the wing, in degrees. Zero is no sweep, positive angles are swept back. Defaults to zero.
  • dihedral: The dihedral angle of the wing. Positive angles are upward dihedral. Defaults to zero.
  • idrag: Multiplier for the "induced drag" generated by this surface. In general, low aspect wings will generate less induced drag per-AoA than high aspect (glider) wings. This value isn't constrained well by the solution process, and may require tuning to get throttle settings correct in high AoA (approach) situations.
  • effectiveness: Multiplier for the "normal" drag generated by the wing. Defaults to 1. Arbitrary, dimensionless factor.
  • camber: The lift produced by the wing at zero angle of attack, expressed as a fraction of the maximum lift produced at the stall AoA.


These defines the horizontal stabilizer of the aircraft. Internally, it is just a wing object and therefore works the same in XML. You are allowed only one hstab object; the solver needs to know which wing's incidence to play with to get the aircraft trimmed correctly.


A "vertical" stabilizer. Like hstab, this is just another wing, with a few special properties. The surface is not "mirrored" as are wing and hstab objects. If you define a left wing only, you'll only get a left wing. The default dihedral, if unspecified, is 90 degrees instead of zero. But all parameters are equally settable, so there's no requirement that this object be "vertical" at all. You can use it for anything you like, such as extra wings for biplanes. Most importantly, these surfaces are not involved with the solver computation, so you can have none, or as many as you like.


A mirrored horizontal stabilizer. Exactly the same as wing, but not involved with the solver computation, so you can have none, or as many as you like.


A subelement of a wing (or hstab/vstab/mstab) that specifies the stall behavior.

  • aoa: The stall angle (maximum lift) in degrees. Note that this is relative to the wing, not the fuselage (since the wing may have a non-zero incidence angle).
  • width: The "width" of the stall, in degrees. A high value indicates a gentle stall. Low values are viscious for a non-twisted wing, but are acceptable for a twisted one (since the whole wing will not stall at the same time).
  • peak: The height of the lift peak, relative to the post-stall secondary lift peak at 45 degrees. Defaults to 1.5. This one is deep voodoo, and probably doesn't need to change much. Bug me for an explanation if you're curious.

flap0, flap1, slat, spoiler

These are subelements of wing/hstab/vstab objects, and specify the location and effectiveness of the control surfaces.

  • start: The position along the wing where the control surface begins.Zero is the root, one is the tip.
  • end: The position where the surface ends, as above.
  • lift: The lift multiplier for a flap or slat at full extension. One is a no-op, a typical aileron might be 1.2 or so, a giant jetliner flap 2.0, and a spoiler 0.0. For spoilers, the interpretation is a little different -- they spoil only "prestall" lift. Lift due purely to "flat plate" effects isn't affected. For typical wings that stall at low AoA's essentially all lift is pre-stall and you don't have to care. Jet fighters tend not to have wing spoilers, for exactly this reason. This value is not applicable to slats, which affect stall AoA only.
  • drag: The drag multiplier, as above. Typically should be higher than the lift multiplier for flaps.
  • aoa: Applicable only to slats. This indicates the angle by which the stall AoA is translated by the slat extension.



A very simple "thrust only" engine object. Useful for things like thrust vectoring nozzles. All it does is map its THROTTLE input axis to its output thrust rating. Does not consume fuel, etc...

  • thrust: Maximum thrust in pounds
  • x,y,z: The point on the airframe where thrust will be applied.
  • vx,vy,vy: The direction of the thrust in airframe coordinates. The vector will be normalized automatically, so any non-zero vector will work fine.


A turbojet/fan engine. It accepts a <control> subelement to map a property to its throttle setting, and an <actionpt> subelement to place the action point of the thrust at a different position than the mass of the engine.

  • x,y,z: The location of the engine, as a point mass. If no actionpt is specified, this will also be the point of application of thrust.
  • mass: The mass of the engine, in pounds.
  • thrust: The maximum sea-level thrust, in pounds.
  • afterburner: Maximum total thrust with afterburner/reheat, in pounds [defaults to "no additional thrust"].
  • rotate: Vector angle of the thrust in degrees about the Y axis [0].
  • n1-idle: Idling low pressure core / fan speed [55].
  • n1-max: Maximum low pressure core / fan speed [102].
  • n2-idle: Idling high pressure core speed [73].
  • n2-max: Maximum high pressure core speed [103].
  • tsfc: Thrust-specific fuel consumption [0.8]. This should be considerably lower for modern turbofans.
  • atsfc: (version >= 2016.3.1) Thrust specific fuel consumption with afterburner on. When set to zero defaults to older behaviour where it is calculated from dry fuel consumption [0].
  • egt: Exhaust gas temperature at takeoff in K [1050].
  • epr: Engine pressure ratio at takeoff [3.0].
  • exhaust-speed: The maximum exhaust speed in knots [~1555].
  • spool-time: Time, in seconds, for the engine to respond to 90% of a commanded powersetting.


A propeller. This element requires an engine subtag. Currently <piston-engine> and <turbine-engine> are supported.

  • x,y,z: The position of the mass (!) of the engine/propeller combination. If the point of force application is different (and it will be) it should be set with an <actionpt> subelement.
  • mass: The mass of the engine/propeller, in pounds.
  • moment: The moment, in kg-metres^2. This has to be hand calculated and guessed at for now. A more automated system will be forthcoming. Use a negative moment value for counter-rotating ("European" -- CCW as seen from behind the prop) propellers. A good guess for this value is the radius of the prop (in metres) squared times the mass (kg) divided by three; that is the moment of a plain "stick" bolted to the prop shaft.
  • radius: The radius, in metres, or the propeller.
  • cruise-speed: The max efficiency cruise speed of the propeller. Generally not the same as the aircraft's cruise speed.
  • cruise-rpm: The RPM of the propeller at max-eff. cruise.
  • cruise-power: The power sunk by the prop at cruise, in horsepower.
  • cruise-alt: The reference cruise altitude in feet.
  • takeoff-power: The takeoff power required by the propeller...
  • takeoff-rpm: ...at the given takeoff RPM.
  • min-rpm: The minimum operational RPM for a constant speed propeller. This is the speed to which the prop governor will seek when the blue lever is at minimum. The coarse-stop attribute limits how far the governor can go into trying to reach this RPM.
  • max-rpm: The maximum operational RPM for a constant speed propeller. See above. The fine-stop attribute limits how far the governor can go in trying to reach this RPM.
  • fine-stop: The minimum pitch of the propeller (high RPM) as a ratio of ideal cruise pitch. This is set to 0.25 by default -- a higher value will result in a lower RPM at low power settings (e.g. idle, taxi, and approach).
  • coarse-stop: The maximum pitch of the propeller (low RPM) as a ratio of ideal cruise pitch. This is set to 4.0 by default -- a lower value may result in a higher RPM at high power settings.
  • gear-ratio: The factor by which the engine RPM is multiplied to produce the propeller RPM. Optional (defaults to 1.0).
  • contra: When set (contra="1"), this indicates that the propeller is a contra-rotating pair. It will not contribute to the aircraft's net gyroscopic moment, nor will it produce asymmetric torque on the aircraft body. Asymmetric slipstream effects, when implemented, will also be zero when this is set.
  • piston-engine: A piston engine definition. This must be a subelement of an enclosing <propeller> tag.
  • eng-power: Maximum BHP of the engine at sea level.
  • eng-rpm: The engine RPM at which eng-power is developed
  • displacement: The engine displacement in cubic inches.
  • compression: The engine compression ratio.

Landing gear


Defines a landing gear. Accepts <control> subelements to map properties to steering and braking. Can also be used to simulate floats. Although the coefficients are still called ..fric, it is calculated in fluids as a drag (proportional to the square of the speed). In fluids gears are not considered to detect crashes (as on ground).

  • x,y,z: The location of the fully-extended gear tip.
  • compression: The distance in metres along the "up" axis that the gear will compress.
  • initial-load: The initial load of the spring in multiples of compression. Defaults to 0. (With this parameter a lower spring-constants will be used for the gear-> can reduce numerical problems (jitter)) Note: the spring-constant is varied from 0% compression to 20% compression to get continuous behavior around 0 compression. (could be physically explained by wheel deformation)
  • upx/upy/upz: The direction of compression, defaults to vertical (0,0,1) if unspecified. These are used only for a direction -- the vector need not be normalized, as the length is specified by "compression".
  • sfric: Static (non-skidding) coefficient of friction. Defaults to 0.8.
  • dfric: Dynamic friction. Defaults to 0.7.
  • spring: A dimensionless multiplier for the automatically generated spring constant. Increase to make the gear stiffer, decrease to make it squishier.
  • damp: A dimensionless multiplier for the automatically generated damping coefficient. Decrease to make the gear "bouncier", increase to make it "slower". Beware of increasing this too far: very high damping forces can make the numerics unstable. If you can't make the gear stop bouncing with this number, try increasing the compression length instead.
  • on-water: if this is set to "0" the gear will be ignored if on water. Defaults to "0"
  • on-solid: if this set to "0" the gear will be ignored if not on water. Defaults to "1"
  • speed-planing:
  • spring-factor-not-planing: At zero speed the spring factor is multiplied by spring-factor-not-planing. Above speed-planing this factor is equal to 1. The idea is, to use this for floats simulating the transition from swimming to planing. speed-planing defaults to 0, spring-factor-not-planing defaults to 1.
  • reduce-friction-by-extension: at full extension the friction is reduced by this relative value. 0.7 means 30% friction at full extension. If you specify a value greater than one, the friction will be zero before reaching full extension. Defaults to "0"
  • ignored-by-solver: with the on-water/on-solid tags you can have more than one set of gears in one aircraft, If the solver (who automatically generates the spring constants) would take all gears into account, the result would be wrong. E. G. set this tag to "1" for all gears, which are not active on runways. Defaults to "0". You can not exclude all gears in the solving process.


Defines a catapult launchbar or strop.

  • x,y,z: The location of the mount point of the launch bar or strop on the aircraft.
  • length: The length of the launch bar from mount point to tip
  • down-angle: The max angle below the horizontal the launchbar can achieve.
  • up-angle: The max angle above the horizontal the launchbar can achieve.
  • holdback-{x,y,z}: The location of the holdback mount point on the aircraft.
  • holdback-length: The length of the holdback from mount point to tip. Note: holdback up-angle and down-angle are the same as those defined for the launchbar and are not specified in the configuration.



A fuel tank. Tanks in the aircraft are identified numerically (starting from zero), in the order they are defined in the file. If the left tank is first, "tank[0]" will be the left tank.

  • x,y,z: The location of the tank.
  • capacity: The maximum contents of the tank, in pounds. Not gallons -- YASim supports fuels of varying densities.
  • jet: A boolean. If present, this causes the fuel density to be treated as Jet-A. Otherwise, gasoline density is used. A more elaborate density setting (in pounds per gallon, for example) would be easy to implement. Bug me.

Center of Gravity


This is a mechanism for modifying the mass distribution of the aircraft. A ballast setting specifies that a particular amount of the empty weight of the aircraft must be placed at a given location. The remaining non-ballast weight will be distributed "intelligently" across the fuselage and wing objects. Note again: this does NOT change the empty weight of the aircraft.

  • x,y,z: The location of the ballast.
  • mass: How much mass, in pounds, to put there. Note that this value can be negative. I find that I often need to "lighten" the tail of the aircraft.


This is an added weight, something not part of the empty weight of the aircraft, like passengers, cargo, or external stores. The actual value of the mass is not specified here, instead, a mapping to a property is used. This allows external code, such as the panel, to control the weight (loading a given cargo configuration from preference files, dropping bombs at runtime, etc...)

  • x,y,z: The location of the weight.
  • mass-prop: The name of the fgfs property containing the mass, in pounds, of this weight.
  • size: The aerodynamic "size", in metres, of the object. This is important for external stores, which will cause drag. For reasonably aerodynamic stuff like bombs, the size should be roughly the width of the object. For other stuff, you're on your own. The default is zero, which results in no aerodynamic force (internal cargo).
  • solve-weight: Subtag of approach and cruise parameters. Used to specify a non-zero setting for a <weight> tag during solution. The default is to assume all weights are zero at the given performance numbers.
  • idx: Index of the weight in the file (starting with zero).
  • weight: Weight setting in pounds.



This element manages a mapping from fgfs properties (user input) to settable values on the aircraft's objects. Note that the value to be set MUST (!) be valid on the given object type. This is not checked for by the parser, and will cause a runtime crash if you try it. Wing's don't have throttle controls, etc... Note that multiple axes may be set on the same value. They are summed before setting.

  • axis: The name of the double-valued fgfs property "axis" to use as input, such as "/controls/flight/aileron".
  • control: Which control axis to set on the objects. It can have the following values:
    • THROTTLE - The throttle on a jet or propeller.
    • MIXTURE - The mixture on a propeller.
    • REHEAT - The afterburner on a jet
    • PROP - The propeller advance
    • BRAKE - The brake on a gear.
    • STEER - The steering angle on a gear.
    • INCIDENCE - The incidence angle of a wing.
    • FLAP0 - The flap0 deflection of a wing.
    • FLAP1 - The flap1 deflection of a wing.
    • SLAT - The slat extension of a wing.
    • SPOILER - The spoiler extension for a wing.
    • CYCLICAIL - The "aileron" cyclic input of a rotor
    • CYCLICELE - The "elevator" cyclic input of a rotor
    • COLLECTIVE - The collective input of a rotor
    • ROTORENGINEON - If not equal zero the rotor is rotating
    • WINCHRELSPEED - The relative winch speed
    • {... and many more, see ControlMap.cpp ...}
  • invert: Negate the value of the property before setting on the object.
  • split: Applicable to wing control surfaces. Sets the normal value on the left wing, and a negated value on the right wing.
  • square: Squares the value before setting. Useful for controls like steering that need a wide range, yet lots of sensitivity in the center. Obviously only applicable to values that have a range of [-1:1] or [0:1].
  • src0/src1/dst0/dst1: If present, these define a linear mapping from the source to the output value. Input values in the range src0-src1 are mapped linearly to dst0-dst1, with clamping for input values that lie outside the range.


This can be used to pass the value of a YASim control axis (after all mapping and summing is applied) back to the property tree.

  • control: Name of the control axis. See above.
  • prop: Property node to receive the value.
  • side: Optional, for split controls. Either "right" or "left"
  • min/max: Clamping applied to output value.


Some controls (most notably flaps and hydraulics) have maximum slew rates and cannot respond instantly to pilot input. This can be implemented with a control-speed tag, which defines a "transition time" required to slew through the full input range. Note that this tag is semi-deprecated, complicated control input filtering can be done much more robustly from a Nasal script.

  • control: Name of the control axis. See above.
  • transition-time: Time in seconds to slew through input range.


This tag is used to define a particular setting for a control axis inside the <cruise> or <approach> tags, where obviously property input is not available. It can be used, for example, to inform the solver that the approach performance values assume full flaps, etc...

  • axis: Name of the control input (i.e. a property name)
  • value: Value of the control axis.

Winch and Aerotow


A hitch, can be used for winch-start (in gliders) or aerotow (in gliders and motor aircraft) or for external cargo with helicopter. You can do aerotow over the net via multiplayer (see j3 and bocian as an example).

  • name: the name of the hitch. must be aerotow if you want to do aerotow via multiplayer. You will find many properties at /sim/hitches/name. Most of them are directly tied to the internal variables, you can modify them as you like. You can add a listener to the property "broken", e. g. for playing a sound.
  • x,y,z: The position of the hitch
  • force-is-calculated-by-other: if you want to simulate aerotowing over the internet, set this value to "1" in the motor aircraft. Don't specify or set this to zero in gliders. In a LAN the time lag might be small enough to set it on both aircraft to "0". It's intended, that this is done automatically in the future.


The tow used for aerotow or winch. This must be a subelement of an enclosing <hitch> tag.

  • length: upstretched length in metres
  • weight-per-meter: in kg/metre
  • elastic-constant: lower values give higher elasticity
  • break-force: in N
  • mp-auto-connect-period: the every x seconds a towed multiplayer aircraft is searched. If found, this tow is connected automatically, parameters are copied from the other aircraft. Should be set only in the motor aircraft, not in the glider


The tow used for aerotow or winch. This must be a subelement of an enclosing <hitch> tag.

  • max-tow-length: in m
  • min-tow-length: in m
  • initial-tow-length: in m. The initial tow length also defines the length/search radius used for the mp-autoconnect feature
  • max-winch-speed: in m/s
  • power: in kW
  • max-force: in N


dc6 fdm in Blender
To make the programmed aircraft visible it is possible to load and compare it with the 3D model within Blender. The applaud for this very usefull script goes to M. Franz, thank you very much!

For Blender versions <= 2.4 the script is located in FlightGears source code utils/Modeller/yasim_import.py.

For Blender versions newer than 2.4, please see Blender YASim import.

The howto, taken from inside the script:

yasim_import.py loads and visualizes a YASim FDM geometry

It is recommended to load the model superimposed over a greyed out and immutable copy of the aircraft model:

  (0) put this script into ~/.blender/scripts/
  (1) load or import aircraft model (menu -> "File" -> "Import" -> "AC3D (.ac) ...")
  (2) create new *empty* scene (menu -> arrow button left of "SCE:scene1" combobox -> "ADD NEW" -> "empty")
  (3) rename scene to yasim (not required)
  (4) link to scene1 (F10 -> "Output" tab -> arrow button left of text entry "No Set Scene" -> "scene1")
  (5) now load the YASim config file (menu -> "File" -> "Import" -> "YASim (.xml) ...")

This is good enough for simple checks. But if you are working on the YASim configuration, then you need a
quick and convenient way to reload the file. In that case continue after (4):

  (5) switch the button area at the bottom of the blender screen to "Scripts Window" mode (green python snake icon)
  (6) load the YASim config file (menu -> "Scripts" -> "Import" -> "YASim (.xml) ...")
  (7) make the "Scripts Window" area as small as possible by dragging the area separator down
  (8) optionally split the "3D View" area and switch the right part to the "Outliner"
  (9) press the "Reload YASim" button in the script area to reload the file

If the 3D model is displaced with respect to the FDM model, then the <offsets> values from the
model animation XML file should be added as comment to the YASim config file, as a line all by
itself, with no spaces surrounding the equal signs. Spaces elsewhere are allowed. For example:



Possible variables are:

  x ... <x-m>
  y ... <y-m>
  z ... <z-m>
  h ... <heading-deg>
  p ... <pitch-deg>
  r ... <roll-deg>

Of course, absolute FDM coordinates can then no longer directly be read from Blender's 3D view.
The cursor coordinates display in the script area, however, shows the coordinates in YASim space.
Note that object names don't contain XML indices but element numbers. YASim_hstab#2 is the third
hstab in the whole file, not necessarily in its parent XML group. A floating point part in the
object name (e.g. YASim_hstab#2.004) only means that the geometry has been reloaded that often.
It's an unavoidable consequence of how Blender deals with meshes.

Elements are displayed as follows:

  cockpit                             -> monkey head
  fuselage                            -> blue "tube" (with only 12 sides for less clutter); center at "a"
  vstab                               -> red with yellow flaps
  wing/mstab/hstab                    -> green with yellow flaps/spoilers/slats (always 20 cm deep);
                                         symmetric surfaces are only displayed on the left side
  thrusters (jet/propeller/thruster)  -> dashed line from center to actionpt;
                                         arrow from actionpt along thrust vector (always 1 m long);
                                         propeller circle
  rotor                               -> radius and rel_len_blade_start circle, direction arrow,
                                         normal and forward vector, one blade at phi0
  gear                                -> contact point and compression vector (no arrow head)
  tank                                -> cube (10 cm side length)
  weight                              -> inverted cone
  ballast                             -> cylinder
  hitch                               -> circle (10 cm diameter)
  hook                                -> dashed line for up angle, T-line for down angle
  launchbar                           -> dashed line for up angles, T-line for down angles

A note about step (0) for Windows users: the mentioned path is inside the folder where Blender lives, something like C:\Program Files\Blender Foundation\Blender\.blender\scripts.

Command Line


By using the standard command line, we can see what the YASim solver is calculating. First, open up Command Prompt, enter in the location of yasim.exe, and then the location of the YASim XML file. For example, here's what you would type in for a standard Windows FlightGear 2.12.0 installation, and viewing the F-14B's YASim file.

Note  You can copy & paste the examples into Command Prompt by right-clicking on the title and navigate to Edit > Paste. Then, click Enter to execute.

"C:\Program Files\FlightGear\bin\Win32\yasim.exe" "C:\Program Files\FlightGear\data\Aircraft\f-14b\f-14b-yasim.xml"

The results will give many different values.

  • Drag Coefficient: The drag coefficient of the aircraft.
  • Lift Ratio: The lift ratio of the aircraft.
  • Cruise AoA: The cruise AoA, from conditions at <cruise> in the xml file.
  • Tail Incidence: The incidence angle of the tail, "solved" by YASim as a way to stabilize the aircraft.
  • Approach Elevator: The approach elevator, from conditions at <approach> in the xml file.
  • CG: Center of gravity of the aircraft in coordinates. Unless it's supposed to be offset, it should always have a Y value of 0.

The YASim standalone solver also has some command line flags that change it's behaviour.

"C:\Program Files\FlightGear\bin\Win32\yasim.exe" "C:\Program Files\FlightGear\data\Aircraft\f-14b\f-14b-yasim.xml" -g -a 1000 -s 490

  • -g: Instructs YASim to generate space-separated tabular data instead of the usual solver output. This can be redirected to a file and used in various plotting programs to visualize the actual lift, drag, L/D curves. The columns of the output from left to right are: AoA, Lift, Drag, L/D. (aoa in degrees, lift and drag in G's).
  • -a <altitude in meter:> Run the solver at the given altitude in meter.
  • -s <speed in knots>: Also run at the given airspeed in knots.
Note  The values generated by this method are for the aircraft taken as a whole, as solved by YASim, so they differ from the values of the wing airfoil.

To get the tabular output for the example above at 1000 m and 150 knots, and to redirect this to a file, one would issue:

"C:\Program Files\FlightGear\bin\Win32\yasim.exe" "C:\Program Files\FlightGear\data\Aircraft\f-14b\f-14b-yasim.xml" -g -a 1000 -s 150 > "C:\Program Files\FlightGear\yasim.txt"

YASim design notes

Andy Ross's original design notes for YASim can be found in this PDF file. These provide some useful background for how YASim works.

New features and bugfixes in version 2017.2

The following is under development and hopefully finds its way into FG version 2017.2

XML parser

support for metric and imperial units

To make life easier for aircraft developers, the parser supports new additional attributes with a unit suffix, e.g. speed-kt for knots and speed-kmh for kilometers per hour.

  • <airplane {mass, mass-lbs, mass-kg}="12345" >
  • <approach {speed, speed-kt, speed-kmh}="123" >
  • <cruise {speed, speed-kt, speed-kmh}="123" >
  • <solve-weight {weight, weight-lbs, weight-kg}="123" >
  • <jet {mass, mass-lbs, mass-kg}="1234" >
  • <tank {capacity, capacity-lbs, capacity-kg}="12345" >
  • <ballast {mass, mass-lbs, mass-kg}="1234" >
Note  Aircraft using this new attributes will not run on older versions of FlightGear, so it is probably wise to publish those only after a reasonable number of users switched version 2017.2 or newer.

CG tuning help

Note  The feature described in this section is not fully implemented yet, however, it may be of some help already.

It is currently implemented for the yasim CLI tool only. It does not affect the airplane behaviour while running FlightGear.

New attributes have been added to <airplane> to assist tuning the center of gravity (CG). The CG position is often expressed relative to the MAC of the wing in percent. You can specify a desired range for CG in % relative to MAC, it will show up in the output of the yasim CLI tool (see example below):

  • cg-min: default 25% (just a guess, better numbers are welcome)
  • cg-max: default 30% (just a guess, better numbers are welcome)
  • auto-ballast: not implemented yet
Note  By convention 0% is leading edge, 100% is trailing edge, however the absolute values on x-axis are the other way round, e.g. nose is +x, tail is -x
Warning  The MAC calculation currently works only on the <wing> element. Numbers will be wrong, if your model uses a combination of <wing> and <mstab> to build a wing with two or more segments.

YASim will print the leading edge coordinates of the MAC (x,y) and its length.

Example output

$ yasim Citation-II-yasim.xml 
This aircraft uses yasim version '2017.2'                                                                                                                                                                                                                                      
= YASim solution results =                                                                                                                                                                                                                                                     
       Iterations: 2210                                                                                                                                                                                                                                                        
 Drag Coefficient: 12.304669                                                                                                                                                                                                                                                   
       Lift Ratio: 85.317558                                                                                                                                                                                                                                                   
       Cruise AoA: 4.016746 deg                                                                                                                                                                                                                                                
   Tail Incidence: -3.053278 deg                                                                                                                                                                                                                                               
Approach Elevator: -0.377542                                                                                                                                                                                                                                                   
               CG: x:-6.543, y:-0.000, z:0.044                                                                                                                                                                                                                                 
    Wing MAC (*1): x:-6.00, y:3.83, length:2.0                                                                                                                                                                                                                                 
    CG-x rel. MAC: 0.272                                                                                                                                                                                                                                                       
    CG-x  desired: -6.599 < -6.543 < -6.198                                                                                                                                                                                                                                    
Inertia tensor [kg*m^2], origo at CG:                                                                                                                                                                                                                                          
  18009.289,  -0.000, 7120.470                                                                                                                                                                                                                                                 
   -0.000, 42459.316,   0.000                                                                                                                                                                                                                                                  
  7120.470,   0.000, 56980.656                                                                                                                                                                                                                                                 
(*1) MAC calculation works on <wing> only! Numbers will be wrong for segmented wings, e.g. <wing>+<mstab>.

Export of YASim internals to property tree

Ever wondered what is going on inside yasim? See the property tree under /fdm/yasim/

Some information is static and shows what yasim has compiled from your XML. Other information is "run-time" like forces, speed, acceleration, c.g. If note noted otherwise, expect metric unit (meter, kilogram, newton, ...).

Path Description Information type
accelerations/ linear and rot. accelerations in aircraft coord. run time
forces/ aerodynamic forces in N run time
velocities/ linear and rot. velocities in aircraft coord. run time
model/cg-x-range-aft desired CG range compile time
model/cg-x-range-front desired CG range compile time
model/cg-x-max CG hard limit from gear position compile time
model/cg-x-min CG hard limit from gear position compile time
model/masses shows the calculated mass points compile time
model/wings wing parameters compile time

Aircraft developer helpers

The command line utility got some new options. For some strange reason, the -a parameter expects altitude in meters instead of ft. This is now visible in the usage message but left unchanged for compatibility.

  yasim <aircraft.xml> [-g [-a meters] [-s kts] [-approach | -cruise] ]
  yasim <aircraft.xml> [-d [-a meters] [-approach | -cruise] ]
  yasim <aircraft.xml> [-m]
  -g print lift/drag table: aoa, lift, drag, lift/drag 
  -d print drag over TAS: kts, drag
     -a set altitude in meters!
     -s set speed in knots
  -m print mass distribution table: id, x, y, z, mass


The following bugfixes require <airplane version="2017.2"> for backward compatibility

  • Ground effect: corrected the calculation of the height where g.e. ends
  • Stall parameters were set wrong for wings with camber=0

Related content

External links