Actions for Active Flow Control on a Boundary-Layer-Ingesting Inlet

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Active Flow Control on a Boundary-Layer-Ingesting Inlet

Author
Jenkins, Luther N.
Published
[2004].
Physical Description
1 electronic document
Additional Creators
Gorton, Susan Althoff, Schuster, Ernest P., Owens, Lewis R., and Allan, Brian G.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
Boundary layer ingestion (BLI) is explored as means to improve overall system performance for Blended Wing Body configuration. The benefits of BLI for vehicle system performance benefit are assessed with a process derived from first principles suitable for highly-integrated propulsion systems. This performance evaluation process provides framework within which to assess the benefits of an integrated BLI inlet and lays the groundwork for higher-fidelity systems studies. The results of the system study show that BLI provides a significant improvement in vehicle performance if the inlet distortion can be controlled, thus encouraging the pursuit of active flow control (AFC) as a BLI enabling technology. The effectiveness of active flow control in reducing engine inlet distortion was assessed using a 6% scale model of a 30% BLI offset, diffusing inlet. The experiment was conducted in the NASA Langley Basic Aerodynamics Research Tunnel with a model inlet designed specifically for this type of testing. High mass flow pulsing actuators provided the active flow control. Measurements were made of the onset boundary layer, the duct surface static pressures, and the mass flow through the duct and the actuators. The distortion was determined by 120 total pressure measurements located at the aerodynamic interface plane. The test matrix was limited to a maximum freestream Mach number of 0.15 with scaled mass flows through the inlet for that condition. The data show that the pulsed actuation can reduce distortion from 29% to 4.6% as measured by the circumferential distortion descriptor DC60 using less than 1% of inlet mass flow. Closed loop control of the actuation was also demonstrated using a sidewall surface static pressure as the response sensor.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20040052867.
AIAA Paper 2004-1203.
42nd AIAA Aerospace Sciences Meeting and Exhibit; 5-8 Jan. 2004; Reno, NV; United States.
Terms of Use and Reproduction
Copyright, Distribution as joint owner in the copyright.
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