In the present work, the CFD analysis and local shape optimization of a boxwing architecture designed during the early stages of the PARSIFAL project are addressed in order to assess and improve its transonic aerodynamic performance. The assessment of the baseline configuration is carried out by means of highfidelity RANS computations while an Euler-based workflow is employed for the optimization study. In both cases, CFD computations are supplemented by a far-field drag post-processing to inspect the behavior and the impact of the different drag sources (induced, wave, pressure and viscous dissipation) on the aerodynamic performance. Results obtained from the optimization of local twist and camber parameters for the isolated boxwing lifting-system are presented and discussed. The optimization successfully achieves a great reduction of the compressibility effects affecting the baseline configuration, leading to a substantial improvement of the aerodynamic performance at cruise and higher values of the lift coefficient.

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