An airflow diverter system for an aircraft may include an external aircraft surface upstream from an engine inlet and a passage having an upstream opening adjacent the engine inlet. The passage may be configured to channel boundary airflow from the external aircraft surface away from the engine inlet. The diverter system may include an occlusion device configured to selectively open and close the opening to the passage.
VARIABLE GEOMETRY FLUSH BOUNDARY DIVERTER
2017-03-09
Patent
Elektronische Ressource
Englisch