An aircraft control structure for drag management includes a nozzle structure configured to exhaust a swirling fluid stream. A plurality of swirl vanes are positioned within the nozzle structure, and an actuation subsystem is configured to cause the plurality of swirl vanes to move from a deployed state to a non-deployed state. In the non-deployed state, the plurality of swirl vanes are substantially flush with the inner surface of the nozzle structure. In the deployed state, the plurality of swirl vanes produce the swirling fluid stream.
Methods and Apparatus for Deployable Swirl Vanes
2017-02-14
Miscellaneous
No indication
English
Constant swirl angle inlet guide vanes
AIAA | 1990
|Anti-swirl vanes for vortex upset alleviation
AIAA | 1999
|Cruise Noise of an Advanced Propeller with Swirl Recovery Vanes
Online Contents | 1993
|