The aeroelastic flight envelops of flying wing aircraft can be extended with a better flow of stresses in the structure. In the present study, we investigate the effect of cross-section configuration on the stress distribution and aeroelastic behavior of a flying wing aircraft. We invoke the constructal law and the principle; the prevention of stress strangulation leads to a wing design associated with the most stable and lightest structure. We used three computer programs Gmsh, VABS (Variational Asymptotic Beam Sectional Analysis), and NATASHA (Nonlinear Aeroelastic Trim And Stability of HALE Aircraft) to study stress distribution and stability of the flying wing aircraft. The results indicate that different wing cross-section designs affect stress distribution as well as the aeroelastic stability of the aircraft. Furthermore, the design with less stress strangulation is associated with a higher flutter speed structure.
