The requirement was to develop 'a definitive model of the original' implying that there would be several interpretations of the plane.
I am assuming that the following baselines are involved:
Implicit is that some baselines, especially those earlier chronologically, will only be worked up to a very basic level. For example, I doubt whether the Concept 1 Baseline was much more than the thought of an idealised shape and structure.
Overall Shape Definition
I used the NACA23012 section scaled to fit the measured sections (ref. Wilson and Carlson) with no washout/in (ref. Wilson).
Initial studies indicated the use of circular arcs. The probable construction being a large semicircle on the bottom and a smaller semicircle on top; these joined by arcs. This is a geometrically simple construction (sans computer).
In plan the fuselage turned out to be similar to the upper surface of the aerofoil section. Again conceptually logical.
The half width of the fuselage developed was 420mm with a shell thickness of 20mm.
The tail format is confusing. It is easy to assume a simple configuration of 120°. However, the angle is 124°.
Still believing in simplicity, I suspect that in practice, the bottom surface is at 60° to the horizontal. (Alternatively, tan 60.25 is 1.75; this is a more practical value than that for 60° (1.732) and hence simplifies any jigging etc).
The numbers are getting too small to verify the truth from my studies.
Panelled Shape definition
The first generation surfaces of the model were as large as possible in order to define the aerodynamic envelope. This later revision into panels (identified from photographs) allowed the model to approach closely with practical reality.
This benefited the wing root fairing especially.
My need now was to integrate the fuselage, empennage and the fairings. The major components were modelled in order to validate their relationships etc. with the aircraft as a whole.
For example, the engine models showed how tight the clearances were between components. For example the forward engine had to be slightly inboard in order to allow the transmission line to be placed outboard of the pilot. Obviously the precise position was determined by the gearbox.
This served to create spatial constraints to an extent. The wing spars were defined and assumed to occupy space which could not be violated. Whilst this is not 100% true any penetrations had to be carried out very carefully.
The holes which can be seen in the photographs of the monocoque fuselage serve to indicate locations and dimensions of components. Those in the fuselage close to the wing trailing edge are particularly interesting in that they suggest an equipment layout change