Cowl assembly for a gas turbine engine

A turbofan engine defining a thickness direction and axial direction, the turbofan engine comprising:

• a turbomachine comprising a compressor section, a combustor section, and a turbine section arranged in serial flow order;
• a fan coupled to be driven by the turbine section;
• and
• a cowl assembly defining at least in part an airflow stream, the cowl assembly comprising a first cowl and a second cowl moveable relative to the first cowl, the first cowl comprising a plurality of first cowl indentations at an end of the first cowl, the second cowl defining an outer surface along the thickness direction and an inner surface along the thickness direction, the second cowl comprising a plurality of second cowl indentations at an end of the second cowl, the plurality of second cowl indentations being complementary in shape to the plurality of first cowl indentations, wherein the plurality of second cowl indentations is positioned locally on the outer surface of the second cowl or locally on the inner surface of the second cowl,
• wherein the second cowl defines an edge at a tip of the inner surface and or at a tip of the outer surface, and wherein the plurality of second cowl indentations is encompassed within a local region spaced from the edge, and wherein the plurality of second cowl indentations are discontinuous around the end of the second cowl.