Engine strut flow control

An aircraft engine comprising:

• an engine core defining an engine axis extending longitudinally;
• a compressor duct located radially outward of the engine core component and directing air therethrough along an airflow direction;
• a strut extending in a radial direction through the compressor duct from an inner end of the strut that is connected to the engine core to an outer end of the strut that is connected to the compressor duct, the strut including a strut body defining an airfoil shape in a cross-sectional plane perpendicular to the radial direction, wherein the airfoil shape includes a leading edge located at an upstream end of the airfoil relative to the airflow direction and a trailing edge located at a downstream end of the airfoil relative to the airflow direction, wherein a chord line is defined as extending through the airfoil in the cross-sectional plane from the leading edge to the trailing edge, and wherein a mid-chord line is defined perpendicular to the chord line at a position along the chord line equidistant between the leading edge and the trailing edges;
• an extraction inlet defined through an exterior surface of the strut body, in fluid communication with an internal conduit of the strut body;
• and
• an injection outlet defined through the exterior surface of the strut body, in fluid communication with the internal conduit for fluid communication through the internal conduit from the extraction inlet to the injection outlet, the injection outlet comprising a first injection outlet and a second injection outlet both in fluid communication with the extraction inlet via the internal conduit, an entirety of the first injection outlet being disposed on one side of the chord line, and an entirety of the second injection outlet being disposed on an opposite side the chord line from the first injection outlet;
• wherein at least one of the extraction inlet and the injection outlet is upstream relative to the other one of the at least one of the extraction inlet and the injection outlet relative to the leading and trailing edges, and
• wherein at least one of the extraction inlet and the injection outlet is downstream of the mid-chord line relative to the leading and trailing edges and configured for mitigation of flow separation in flow around the strut body downstream of the mid-chord line.