[REFACTOR ]update wing_design documentation

Description

Update wing design config regarding:

• icao aerodrome reference code behaviour
• leading-/trailing-edge checks

Related Issue(s)

• N.A.

Other Changes

• N.A.

Screenshots/Logs

-N.A.

Testing Instructions

1. [Step 1: Checkout branch refactor/wing_design_documentation]
2. [Step 2: Run mkdocs serve]
3. [Step 3: Check local page]

Developer Checklist

• Code has been tested locally and/or in pipeline.
• (if applicable) documentation updated.
• (if applicable) impact of new dependencies reviewed and included in project.
• Merge conflicts resolved with the target branch.

Additional Notes

-N.A.

docs/documentation/sizing/wing_design/design-methods.md

@@ -30,7 +30,7 @@ When the aspect ratio is calculated, the tool computes the span of the wing and
       - E: 52m ... < 65m
       - F: 65m ... < 80m
 
-If the limits are exceeded, the user receives a warning and the aspect ratio as well as the span are set to the limit accordingly.
+If the limits are exceeded which are defined in the aircraft exchange file in the requirements and specification block, the user receives a warning, that the current values will not match the requirements.
 
 #### Step 4: Taper ratio computation
 After computing the aspect ratio, the taper ratio can be user defined or determined by a method from Howe. Howe uses the aspect ration and the quarter chord sweep to compute the taper ratio.
@@ -43,9 +43,7 @@ Based on the computed data and the information from the aircraft exchange file,
 
 The algorithm to determine the geometry differs in some points since the kinked geometry has an inner and an outer wing while in the unkinked version, no differentiation between inner and outer wing is done.
 
-The unkinked geometry calculation is straight forward, however the kinked version has an root finding loop to compute the root by keeping the taper ratio, aspect ratio and wing area feasible. Afterwards certain conditions are checked like  $LE_{inner} \ge LE_{outer}$ and $TE_{inner} \le TE_{outer}$.
-
-If those checks succeed, the geometry will be finalized, otherwise the tool throws an error here.
+The unkinked geometry calculation is straight forward, however the kinked version has an root finding loop to compute the root by matching the taper ratio, aspect ratio and wing area.
 
 #### Step 7: Determine spar position and control devices
 The spar positions and control devices can be set by user. For control devices, a basic set of control devices will be set consisting of an aileron, and a number of high lift devices and spoilers for air and ground.