An aerodynamic body defining a chord-wise direction relative to an airflow over the aerodynamic body, comprising: an outer panel skin having an inner surface , an outer surface , and a plurality of perforations extending from the inner surface to the outer surface , the outer panel skin extending around an interior surface of the aerodynamic body and defining a leading edge of the aerodynamic body; and a micro-lattice stiffener structure including: a plurality of main beams each having at least a first end connected to the inner surface of the outer panel skin , and a plurality of diagonal support struts each extending diagonally between and connected to adjacent main beams ; wherein the micro-lattice stiffener structure extends along the inner surface of the outer panel skin downstream of the plurality of perforations , and the plurality of main beams and the plurality of diagonal support struts define airflow gaps there between to place the plurality of perforations in fluid communication with the interior surface of the aerodynamic body downstream from the micro-lattice stiffener structure , wherein the plurality of main beams are arranged in a two-dimensional array on the inner surface of the outer panel skin , wherein each group of four of the plurality of main beams defines corners of a quadrilateral and two of the plurality of diagonal support struts extend between the main beams at adjacent corners of the quadrilateral , with the two of the plurality of diagonal support struts intersecting at nodes along sides of the quadrilateral . an outer panel skin having an inner surface , an outer surface , and a plurality of perforations extending from the inner surface to the outer surface , the outer panel skin extending around an interior surface of the aerodynamic body and defining a leading edge of the aerodynamic body; and a micro-lattice stiffener structure including: a plurality of main beams each having at least a first end connected to the inner surface of the outer panel skin , and a plurality of diagonal support struts each extending diagonally between and connected to adjacent main beams ; a plurality of main beams each having at least a first end connected to the inner surface of the outer panel skin , and a plurality of diagonal support struts each extending diagonally between and connected to adjacent main beams ; wherein the micro-lattice stiffener structure extends along the inner surface of the outer panel skin downstream of the plurality of perforations , and the plurality of main beams and the plurality of diagonal support struts define airflow gaps there between to place the plurality of perforations in fluid communication with the interior surface of the aerodynamic body downstream from the micro-lattice stiffener structure , wherein the plurality of main beams are arranged in a two-dimensional array on the inner surface of the outer panel skin , wherein each group of four of the plurality of main beams defines corners of a quadrilateral and two of the plurality of diagonal support struts extend between the main beams at adjacent corners of the quadrilateral , with the two of the plurality of diagonal support struts intersecting at nodes along sides of the quadrilateral . <EOS>