VARIABLE GEOMETRY INLET FOR TURBOPROPELLER INLET PRESSURE RECOVERY OPTIMIZATION

A turboprop engine (110) includes a main nacelle body (212), a rotatable hub (220) provided on the main nacelle body (212), a plurality of propellers (215, 520) connected to the rotatable hub (220), and a nacelle extension (214) coupled to the main nacelle body (212), the nacelle extension (214) including at least one wall (240) defining an air intake inlet (245, 510). The air intake inlet (245, 510) is movable in an airflow axis with respect to a trailing edge (216, 521) of a propeller (215, 520) in the plurality of propellers (215, 520) to vary a distance between the air intake inlet (245, 510) and the trailing edge (216, 521) of the propeller (215, 520) during various phases of operation of the turboprop engine (110).