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Active Flow Control on Vertical Tail ModelsActive flow control (AFC) subscale experiments were conducted at the Lucas Wind Tunnel of the California Institute of Technology. Tests were performed on a generic vertical tail model at low speeds. Fluidic oscillators were used at the trailing edge of the main element (vertical stabilizer) to redirect the flow over the rudder and delay or prevent flow separation. Side force increases in excess of 50% were achieved with a 2% momentum coefficient (C(sub μ)) input. The results indicated that a collective C(sub μ) of about 1% could increase the side force by 30–50%. This result is achieved by reducing the spanwise flow on the swept back wings that contributes to early flow separation near their tips. These experiments provided the technical backdrop to test the full-scale Boeing 757 vertical tail model equipped with a fluidic oscillator system at the National Full-scale Aerodynamics Complex 40-by 80-foot Wind Tunnel, NASA Ames Research Center. The C(sub μ) is shown to be an important parameter for scaling a fluidic oscillator AFC system from subscale to full-scale wind tunnel tests. The results of these tests provided the required rationale to use a fluidic oscillator AFC configuration for a follow-on flight test on the Boeing 757 ecoDemonstrator.
Document ID
20190028388
Acquisition Source
Langley Research Center
Document Type
Reprint (Version printed in journal)
External Source(s)
doi:10.2514/1.J057876
Authors
Andino, Marlyn Y. (NASA Langley Research Center Hampton, VA, United States)
Lin, John C. (NASA Langley Research Center Hampton, VA, United States)
Roman, Seele (General Electric Aviation Cincinnati, OH, United States)
Graff, Emilio C. (Shaper Tools, Inc. San Francisco, CA, United States)
Gharib, Mory (California Institute of Technology (CalTech) Pasadena, CA, United States)
Whalen, Edward A. (Boeing Company Fairborn, OH, United States)
Wygnanski, Israel J. (Arizona Univ. Tucson, AZ, United States)
Date Acquired
August 1, 2019
Publication Date
July 17, 2019
Publication Information
Publication: AIAA Journal
Publisher: American Institute of Aeronautics and Astronautics
Volume: 57
Issue: 8
ISSN: 0001-1452
e-ISSN: 1533-385X
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NF1676L-29550
Funding Number(s)
WBS: 081876.02.07.02.01.04
PROJECT: ARMD_081876
Distribution Limits
Public
Copyright
Public Use Permitted.

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