Inlet vane forward of aircraft propulsion system airflow inlet

An assembly for an aircraft, comprising:

• an airframe structure including a fuselage and at least two wings, the fuselage extending longitudinally along a longitudinal centerline from a forward end of the fuselage to an aft end of the fuselage, and the at least two wings extending laterally from opposing sides of the fuselage;
• a propulsion system mounted to the airframe structure, the propulsion system including an airflow inlet into the propulsion system, and the airflow inlet spaced vertically out from a top side of the airframe structure;
• and
• a vane projecting vertically out from the top side of the airframe structure to a distal end of the vane, the vane laterally overlapping and longitudinally forward of the airflow inlet;
• wherein the airflow inlet is spaced vertically out from the top side of the airframe structure by a vertical distance;
• and
• wherein a quotient of the vertical distance divided by a maximum vertical height of the vane is between 0.25 and 40.

An assembly for an aircraft, comprising:

• an airframe structure including a fuselage and at least two wings, the fuselage extending longitudinally along a longitudinal centerline from a forward end of the fuselage to an aft end of the fuselage, and the at least two wings extending laterally from opposing sides of the fuselage;
• a propulsion system mounted to the airframe structure, the propulsion system including an airflow inlet into the propulsion system, and the airflow inlet spaced vertically out from a top side of the airframe structure;
• and
• a vane projecting vertically out from the top side of the airframe structure to a distal end of the vane, the vane laterally overlapping and longitudinally forward of the airflow inlet;
• wherein a length of the vane extends from a leading edge of the vane to a trailing edge of the vane;
• and
• wherein a quotient of a maximum thickness of the vane divided by the length of the vane is between 0.05 and 0.2.