I am trying to understand wing_thickness_ratio and how it’s expressed? My

original assumption was it was the airfoil thickness ratio express as percent

over 100. If we use a NACA0012 airfoil as example it has a thickness ratio of

12(0.12 in the cfg), which ends up with a very THICC “wing” element. If we

check the documentation:

https://docs.flightsimulator.com/html/Content_Configuration/SimObjects/Aircraft_SimO/flight_model/geometry.htm

it states:

```
The wing local thickness, calculated as: localchord(x)* wingthicknessratio
where: x=lateral chord
Value is in ft.
```

Given their fomula and solving for the thickness ratio thickness ratio = local

thickness / local chord thickness ratio = 12/100 thickness ratio = 0.12 Which

is our AirFoil Thickness, however when viewed in the Sim with Sim Forces

debug, the green dots do not align with the wing surfaces and there is quite a

lot of free air between the surface and the dots. If we review the “tutorial”

on creating a flight model:

https://docs.flightsimulator.com/html/mergedProjects/How_To_Make_An_Aircraft/Contents/Files/Flight_Model/Geometry.htm

it states:

```
Next you can set the Thickness Ratio of the wing in the Geometry panel. This is a ratio of the wing size and most wings are between 2% and 5% thick. In the CFG file, this is the wing_thickness_ratio parameter .
```

There are many many aircraft out there using airfoils with thickness ratio

well above 5% so it must mean something else. During a discussion on our

discord, one of our members thought perhaps that it is the % thickness ABOVE

the camber line.

```
Maybe they divide by 2. and they mean the thickness is from the camber line to the top of the airfoil. then 0.05 would be 0.10 (10%) getting closer.
```

If we continue with our NACA0012 example this has a 0 camber so runs through

centreline and the thickness would then be expressed as 6% (thickness -

camber) / 2 (12 - 0) / 2 = 6 This appears to be closer to what is requested.

If we use something a little more exotic with say a 12% thickness and 1.5%

camber: (12-1.5)/2 = 5.25% Unfortunately all of this is just guessing. So how

do we reliably calculate `wing_thickness_ratio`

?