Systems and methods for lifter motor cooling in evtol aircraft

An apparatus for aircraft propulsion, comprising:

• a propeller;
• an electric engine mounted to a support structure having a longitudinal axis through the center of the support structure, wherein the electric engine is configured to rotate a propeller, the electric engine being located within an enclosure;
• a first heat transfer element that is thermally coupled to the electric engine, wherein at least part of the first heat transfer element is located external to the enclosure;
• a first air inlet located at an upper side of the support structure, wherein the first air inlet is configured to receive downwash from the propeller during a lift phase, and wherein the first air inlet is radially offset from a hub of the electric engine and the first air inlet is laterally offset from the longitudinal axis, wherein an amount of the lateral offset positions the first air inlet in a region of high downwash pressure or airflow;
• a first cooling path configured to direct a first portion of the downwash from the first air inlet to the first heat transfer element;
• and
• a first air outlet configured to exhaust the first portion of the downwash from the first heat transfer element.