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
2022-06-22
Patent
Electronic Resource
English
Optimised Tooth Flank Geometry for High Performance Transmissions
SAE Technical Papers | 2007
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