Patent Number: 7,784,732

Title: Boundary-layer-ingesting inlet flow control system

Abstract: A system for reducing distortion at the aerodynamic interface plane of a boundary-layer-ingesting inlet using a combination of active and passive flow control devices is disclosed. Active flow control jets and vortex generating vanes are used in combination to reduce distortion across a range of inlet operating conditions. Together, the vortex generating vanes can reduce most of the inlet distortion and the active flow control jets can be used at a significantly reduced control jet mass flow rate to make sure the inlet distortion stays low as the inlet mass flow rate varies. Overall inlet distortion, measured and described as average SAE circumferential distortion descriptor, was maintained at a value of 0.02 or less. Advantageous arrangements and orientations of the active flow control jets and the vortex generating vanes were developed using computational fluid dynamics simulations and wind tunnel experimentations.

Inventors: Owens; Lewis R. (Williamsburg, VA), Allan; Brian G. (Williamsburg, VA)

Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

International Classification: B64B 1/24 (20060101)

Expiration Date: 8/31/12018