Refinement and analysis of concept

Wing structure layout
航空宇航学院
• Sometimes the spanwise bending and torsion requirements may
be met by a single beam or spar located near to the maximum
chordwise depth of the aerofoil and associated with a shear
carrying leading edge, or 'D' nose, terminating at the spar.
• More usually there are two or more spars located across the
chord, and together with the upper and lower covers between
their chordwise extremities they form a box beam which also
meets the torsion requirement.
• The forward and aft extremities of this beam are determined by
the auxiliary lifting surfaces and ailerons.
• The rearmost spar is often located at 60-70% of the chord,
leaving room for the trailing edge surfaces
Aircraft Conceptual Design