Patent ID: 6179251
Filing Date: 2001-01-30
Classification: B64C,B64D,F02C,Y02T

Abstract:
An aerodynamic turbo engine nacelle, disposable about an engine having an engine face, for mitigating boundary layer separation of intake airflow comprising:an engine inlet having an interior surface and a curved portion having a leading edge, the leading edge defining an interior surface circular area, the interior surface defining a minimum circular area, the engine inlet having a ratio of the interior surface circular area to the minimum circular area less than 1.33; anda pressurized fluid injecting device for injecting pressurized fluid at the engine inlet for mitigating against boundary layer separation at the engine inlet, the pressurized fluid injecting device being aligned to inject pressurized fluid in an direction and at a pressure and velocity to simulate a ratio of the interior surface circular area to the minimum circular area which is greater than 1.33.