Hi

I calculated the whole wing as one.

The aileron caused forces I calculated based to the wing-aileron size and lever arm. End result is a moment around longitudinal axis.

Simple code for the effective AOA calculation

```
# effective aoa with given stab, elev dimensions and elevator deflection angle
from math import degrees, radians, sin, atan, cos
from math import degrees as deg
from math import radians as rad
def rr(v,d=2):
return round(v,d)
def EA(dim,a): # Geometric method
ar = rad(a)
return (deg(atan( (dim[1] * sin(ar)) / ( (dim[1] * cos(ar)) + dim[0] ))))
def I_O(dat,iv): # Interpolation method
return(dat[1] + ((iv - dat[0]) * (dat[3] - dat[1]))/(dat[2] - dat[0]))
# Horizontal stab & elev. dimensions for the geometric method
dim = [0.6, 0.5]
# Dataset for the interpolation method.
# NOTE! Pre-calculated with geometric method
datas = [-32650, -18.1, 32650 , 18.1]
# +/- 32650 is a game input device raw value range
# ------------------------------------------------
# Geometric method
# Give a elevator deflection angle in degrees
a = 40.0
# Interpolation method
# Give a game input device raw value
ca = 32000
print rr(EA(dim,a)),' Geometric method
',rr(I_O(datas,ca)), ' Interpolation method'
```

The elevator have often a Angle of Incidence so, the 0 elevator deflection cause ‘build-in’ force.

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