A compressed gas ejection assembly for a rotating wing aircraft blade comprising a compressed gas passage adapted to allow a substantially constant mass flow through the compressed gas ejection assembly across at least a portion of the width of the compressed gas ejection assembly.
OPTIMISED NOZZLE GEOMETRY
OPTIMIERTE DÜSENGEOMETRIE
GÉOMÉTRIE DE BUSE OPTIMISÉE
22.06.2022
Patent
Elektronische Ressource
Englisch
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