PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL

摘要

A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle.