Aero.dat

The aero.dat configuration file describes the aerodynamic properties of the flight model.

The Silent Wings aerodynamic model works with a "panel model" that describes the geometrical 
design of the aircraft that is to be simulated. By (manually!) dividing an aircraft into 
segments, or "panels", the flight dynamics code can calculate the forces that act 
on the aircraft and let it fly. 

The panel model works with two different panels: wingpanels and fuselage panels. The Wing panels are used to describe the wings and fins on the aircraft. Every wing panel needs an 
airfoil to do the aerodynamic definition, so these airfoils need to be defined as well. 

The airfoils can be shared between panels of the same wing, and are therefor defined 
before the wing panels. You must define one airfoil for each wing (or fin), 
also when they all would use the same airfoil, because the airfoil is defined with 
3-dimensional properties (aspect ratio of wing, etc). 

You may, however, use several airfoils for a single wing, if desired. 

Airfoils: 

An airfoil is defined like this: 

airfoil { 
name = xxx 
profile = xx 
... 
} 

The variables to be defined are: 

name = <string> 
The name of the airfoil. This can be called whatever you like, and is the name to be used in the wing panels. 

profile = <filename> (but without .cd/.cl/.cm extension!) 
The airfoil polar fileset to use. These files are found in the airfoils directory. 
There are 3 files for one airfoil, defining lift (.cl), drag (.cd) and pitch moment 
(.cm), that all have the same name. 

k = <float> 
The "k" factor defines the induced drag finesse of the wing. A setting of 1.0 gives 
the optimum, planar wing with elliptical lift distribution. So any other planar 
wing will have a value higher than 1.0. 

Wings with winglets may get values lower than 1.0. The best wings currently available 
(Antares) have a k factor of 0.95. 

aspectratio = <float> 
The aspect ratio of the wing that will use this airfoil. 

meanchord = <float> 
the mean chord of the wing that will use this airfoil 

cl_adjust = <float> 
This factor can be used to fine-tune the lift curve. The variable is multiplied with 
the lift from the lift polar. Leave this to 1.0 when you start up, and use it 
as a last resort when fine tuning your model. 

cd_adjust = <float> 
This factor can be used to fine-tune the drag curve. The variable is added to the 
drag polar. Use with caution. 

Wing panel: 

A wingpanel is defined with "wingpanel" followed by brackets containing the wing panel 
variables, one variable per line. 

wingpanel { 
name = xxx 
area = xxx 
... 
} 

A wing can be defined with one or several panels. For elevator and rudder surfaces, one 
panel is mostly sufficient. A main wing should have at least 4 panels in total (two left, 
two right). 

When not defined, variables default to zero. That means, if certain things are not to 
be used on the wing panel (such as a spoiler), the variables do not have to be set. 

Please see the example illustration of the Ventus aero model to get a picture of 
how the panels are defined. 

Variable descriptions: 

General data: 

name 
Wing panel name 

airfoil = <text string> 
The airfoil to use. The name to use is the same as defined in one of the airfoil sections. 

position = [ x.x y.y z.z ] 
The panel position coordinate. See the illustration on how to define this point. 

area = <float> 
Wing panel area 

meanchord = <float> 
The mean chord of the wing panel (not the wing!) 

alpha = <float> 
The panel's angle of incident. 

dihedral = <float> 
The panel's dihedral angle. 

sweep = <float> 
The panel's sweep angle. 

propwash = 0.0 to 1.0 
If the panel is positioned behind a propeller, you can set this value higher than 0.0 
to have a propwash effect on the panel. This will for example allow for rudder and 
elevator authority when standing still on the Antares model. 

Control surface variables: (can be left out if the panel has non controls) 
The control system of Silent Wings is quite flexible, and can handle more exotic designs like canards, v-tails and flying wings. You can add all the controllers to have an 
effect on every panel in different ways. 

delta_max = <float> 
The flap's maximum (positive) deflection angle, in degrees. 

delta_min = <float> 
The flap's minimum (negative) deflection angle, in degrees. 

delta_neutral = <float> 
The flap's position when the controls are centered 

aileron_mix = -1.0 to 1.0 
The amount of aileron control that is to be applied to the flap. For the left wing, 
normally 1.0 is used, for the right wing -1.0. For less effect use smaller numbers. For 
no aileron control set to 0.0 or leave it out. 

aileron_delta = <float> 
The maximum difference in deflection between the left and right aileron. For example, 
if with fully deflected ailerons the left one is at +10 and the right one at -10, this value 
should be set to 20.0. 

aileron_diff = <float> 
Aileron differential. This factor will define how much more the up-going (negative) aileron 
will go up compared with the down-going one (positive). The value 1.0 (default) means equal 
deflection in both directions. A setting of 2.0 means the up-going aileron will do 
twice as much deflection as the down-going aileron. This is common on sailplanes as 
it reduces the adverse yaw effect of the ailerons. 

flap_pos = <float> 
If the panel has flap control, set the most positive flap setting in degrees here. 

flap_neg = <float> 
If the panel has flap control, set the most negative flap position in degrees here. 

elevator_mix = -1.0 to 1.0 
The amount of elevator control that is to be applied to the flap. 

rudder_mix = -1.0 to 1.0 
The amount of rudder control that is to be applied to the flap. 

throttle_mix = -1.0 to 1.0 
The amount of throttle control that is to be applied to the flap 
(this is rather uncommon, so it will mostly be left out. It can be used to 
compensate or emulate some throttle effects) 

Spoiler/airbrake variables: (can be left out if the panel has no airbrake or spoiler) 

brake_on = 0 or 1 
Set this variable to 1 to enable the spoiler/airbrake 

brake_surface = <float> 
The surface frontal surface of the fully extended brake. 

brake_liftdest = <float> 
The amount of lift coefficient reduction with a fully extended brake. 
This is normally around 1.0, but must be experimented with. 

brake_cd = <float> 
The drag coefficient of the fully extended brake. 

brake_superp = 0 or 1 
Setting this to 1 enables superpositional mode. With this a brake can be added upon a wing 
and will have an effect on the lift and drag from the other wing panels only when the 
brake controller is on. When set to zero the wing panel is just a normal wing panel, 
that also has an airbrake/spoiler attached. Which to use depends on how the panelling 
of the wing is chosen. 

Fuselage panel: 

The fuselae panel is a model of an aircraft fuselage. Its largest effect is to add 
drag to the aero model. 

It is defined as 

fuselage { 
name = xxx 
position = xxx 
... 
} 

Variable description: 

name = <string> 
Panel name 

position = [ x.x y.y z.z ] 
The panel position. This is the position where the drag force is applied, and does 
influence flight mechanics of your model, especially in spins. Start out by positioning this near to your model's centre of gravity. 

ref_area = <float> 
Reference frontal area of the fuselage 

ref_volume = <float> 
Reference volume of the fuselage. In most cases, this can be set to 1.0. 

cd_front = frontal_drag_filenamename (but without the .cd extension) 
The frontal drag is defined in a name.cd file that is placed in the airfoils directory. 
Use this file to finetune your model's glide polar. 

cd_side = <float> 
Sidewards drag coefficient 

cd_top = <float> 
Top/bottom drag coefficient 

k_y = 0.0 to 1.0 
k_z = 0.0 to 1.0 

These two factors set the magnitude of instability of the fuselage. Try something like 
0.1 first. A larger value means more instability. 

alpha_fuselage = <float> 
The fuselage's angle of incidence. Normally 0.0. 

cd_landinggear = <float> 
The drag of an extended landing gear.