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We continue in this tutorial the work started in Tutorial 1, working on the same specifications. The conclusion of the first tutorial was that a wing area of 10 m² is needed. A rudimentary CAD was done to define the basic architecture of this aircraft.
A mass-and-inertia estimation was done for the main components of the aircraft. The mass, centres of gravity (CoG), and moments of inertia are estimated, for 3 load configurations corresponding to the maximum take-off mass, to the most forward CoG and most backward CoG. The table below shows the results obtained.
