  This paper presents a method for simultaneous optimization of the outer shape
and internal topology of aircraft wings, with the objective of minimizing drag
subject to lift and compliance constraints for multiple load cases. The physics
are evaluated by the means of a source-doublet panel method for the aerodynamic
response and linear elastic finite elements for the structural response, which
are one-way coupled. At each design iteration, a mapping procedure is applied
to map the current wing shape and corresponding pressure loads to the unfitted
finite element mesh covering the design domain. Wings of small fixed-wing
airplanes both with and without a stiffening strut are optimized. The resulting
wings show internal topologies with struts and wall-truss combinations,
depending on the design freedom of the shape optimization. The lift
distributions of the optimized wings show patterns like the ones obtained when
performing optimization of wing shapes with constraints on the bending moment
at the root.
