Disclosed is a flow guide body (19) for an aircraft (1), comprising a main body (29) having an outer aerodynamic surface (33) provided with a plurality of outlet openings (21), and a plurality of flow control devices (31), each flow control device (31) comprising an inlet (35), an interaction chamber (37), a first outlet (39) and a second outlet (41), wherein a first control inlet (53) is connected to the interaction chamber (37) at the first side (49) of the chamber axis (47), wherein the first and second outlets (39, 41) are each connected to outlet openings (21) in the aerodynamic surface (33), wherein the first outlet (39) is provided with a first control outlet (55) and the second outlet (41) is provided with a second control outlet (57), wherein at least one second flow control device (31b) is arranged such that the first or second outlet (39, 41) is connected with the inlet (35) of the first flow control device (31a), wherein one of the first and second control outlets (55, 57) of the first flow control device (31a) is connected to the first control inlet (53) of the first flow control device (31a), and wherein the other of the first and second control outlets (55, 57) of the first flow control device (31a) is connected to the first control inlet (53, 59) of the second flow control device (31b).
FLOW GUIDE BODY WITH FLUIDIC ACTUATOR FOR AN AIRCRAFT
STRÖMUNGSLEITKÖRPER MIT FLUID-AKTUATOR FÜR EIN FLUGZEUG
CORPS DE GUIDAGE D'ÉCOULEMENT AVEC UN ACTUATEUR FLUIDIQUE POUR UN AVION
2020-04-01
Patent
Electronic Resource
English
FLUIDIC ACTUATOR HAVING JET VECTOR CONTROL AND FLOW BODY
European Patent Office | 2018
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