Aerodynamic low drag structure
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United States of America Patent
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Apr 28, 1998
Grant Date -
N/A
app pub date -
Dec 5, 1995
filing date -
Dec 5, 1994
priority date (Note) -
Expired
status (Latency Note)
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Abstract
Boundary layer separation at the boundary surface of an intake duct (18) of a turbofan aeroengine nacelle (12) at conditions of high incidence and high engine mass flow arises from shockwave induced pressure gradients in the boundary layer. To control separation, gaseous fluid is withdrawn from a high pressure region of the boundary layer at a downstream region of the boundary surface, conveyed within the intake duct structure (19) and discharged at an upstream region of the boundary surface into a low pressure region of the boundary layer. The intake duct (18) embodies a noise attenuation panel (19), and fluid is withdrawn from the high pressure region of the boundary layer into a modified panel section (191) by passage through apertures (30) in the front face of the panel section (191) at a downstream region of the panel section, conveyed along a fluid communication path within the panel section (191) and discharged into the low pressure region of the boundary layer by passage through apertures (30) in the front face of the panel section (191) at an upstream region of the panel section (191). Gaseous fluid is conveyed solely as a consequence of the difference in pressures in the boundary layer at the downstream and upstream regions.
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