A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.
Passive boundary layer bleed system for nacelle inlet airflow control
2017-05-09
Patent
Elektronische Ressource
Englisch
Supersonic-inlet boundary-layer bleed flow
AIAA | 1996
|Modeling Supersonic Inlet Boundary-Layer Bleed Roughness
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|On supersonic-inlet boundary-layer bleed flow
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|Modeling supersonic inlet boundary-layer bleed roughness
AIAA | 1993
|Modeling supersonic inlet boundary layer bleed roughness
AIAA | 1992
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