The scaling and fitting algorithms used to 'fit' a sub component to its parent not intuitive, and quite often ends in tweaking numbers until a 'decent' looking aircraft is obtained.
A better method would be to use scaling factors as actual percentages of a reference length, e.g. a wing with an x scaling factor of 0.2 would have 20% of its parents reference x length (wing chord, or fuselage x length).
The scaling and fitting algorithms used to 'fit' a sub component to its parent not intuitive, and quite often ends in tweaking numbers until a 'decent' looking aircraft is obtained.
A better method would be to use scaling factors as actual percentages of a reference length, e.g. a wing with an x scaling factor of 0.2 would have 20% of its parents reference x length (wing chord, or fuselage x length).
This should also fix #8.