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Boundary Layer Flow Control in Low-R...

Kiley, Joshua Michael,

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Boundary Layer Flow Control in Low-Reynolds Numbers via Internal Acoustic Excitation /

Record Type:	Electronic resources : Monograph/item
Title/Author:	Boundary Layer Flow Control in Low-Reynolds Numbers via Internal Acoustic Excitation // Joshua Michael Kiley.
Author:	Kiley, Joshua Michael,
Description:	1 electronic resource (261 pages)
Notes:	Source: Masters Abstracts International, Volume: 86-02.
Contained By:	Masters Abstracts International86-02.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31485516
ISBN:	9798383702185

Boundary Layer Flow Control in Low-Reynolds Numbers via Internal Acoustic Excitation /
Kiley, Joshua Michael,

Boundary Layer Flow Control in Low-Reynolds Numbers via Internal Acoustic Excitation /Joshua Michael Kiley. - 1 electronic resource (261 pages)

Source: Masters Abstracts International, Volume: 86-02.

Aerodynamic flow control using internal acoustic excitation holds promise as it combines the simplicity of passive flow control techniques (in terms of added weight and operational complexity) with the control authority of active flow control methods. While previous studies have analyzed the effects of acoustic excitation on steady wing aerodynamics, the effect of excitation on the unsteady aerodynamics is not known, which is the aim of the current effort. Internally mounted speakers on a symmetric National Advisory Committee for Aeronautics (NACA) 0012 wing are used to excite the unsteady boundary layer at the wing's leading edge as it executes linear pitch motions ranging from quasi-steady (trailing-edge driven stall) to vortex dominated (mixed leading- and trailing-edge driven stall) motions at freestream Reynolds numbers (Re) of 120, 000 and 180, 000. Experimental results show that, while acoustic excitation delays stall for quasi-steady motions, it enhances lift in the linear region and increases leading-edge vortex strength for vortex -dominated motions. The degree of change was observed to be a function of the excitation frequency. The current work establishes the effects of acoustic flow excitation in unsteady, low-Re wing aerodynamics and provides insights on the path forward to effectively implement the method for active flow control.

English

ISBN: 9798383702185Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Acoustic excitation

Boundary Layer Flow Control in Low-Reynolds Numbers via Internal Acoustic Excitation /
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100 1 $a Kiley, Joshua Michael, $e author. $3 3830000
245 1 0 $a Boundary Layer Flow Control in Low-Reynolds Numbers via Internal Acoustic Excitation / $c Joshua Michael Kiley.
264 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2024
300 $a 1 electronic resource (261 pages)
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500 $a Source: Masters Abstracts International, Volume: 86-02.
500 $a Advisors: Narsipur, Shreyas Committee members: Sescu, Adrian; Belk, Davy; Wolz, Robert.
502 $b M.S. $c Mississippi State University $d 2024.
520 $a Aerodynamic flow control using internal acoustic excitation holds promise as it combines the simplicity of passive flow control techniques (in terms of added weight and operational complexity) with the control authority of active flow control methods. While previous studies have analyzed the effects of acoustic excitation on steady wing aerodynamics, the effect of excitation on the unsteady aerodynamics is not known, which is the aim of the current effort. Internally mounted speakers on a symmetric National Advisory Committee for Aeronautics (NACA) 0012 wing are used to excite the unsteady boundary layer at the wing's leading edge as it executes linear pitch motions ranging from quasi-steady (trailing-edge driven stall) to vortex dominated (mixed leading- and trailing-edge driven stall) motions at freestream Reynolds numbers (Re) of 120, 000 and 180, 000. Experimental results show that, while acoustic excitation delays stall for quasi-steady motions, it enhances lift in the linear region and increases leading-edge vortex strength for vortex -dominated motions. The degree of change was observed to be a function of the excitation frequency. The current work establishes the effects of acoustic flow excitation in unsteady, low-Re wing aerodynamics and provides insights on the path forward to effectively implement the method for active flow control.
546 $a English
590 $a School code: 0132
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Acoustics. $3 879105
653 $a Acoustic excitation
653 $a Aerodynamic flow control
653 $a Boundary layer control
653 $a Flow control
653 $a Internal acoustic excitation
653 $a Unsteady aerodynamics
690 $a 0538
690 $a 0986
710 2 $a Mississippi State University. $b Department of Aerospace Engineering. $e degree granting institution. $3 3830001
720 1 $a Narsipur, Shreyas $e degree supervisor.
773 0 $t Masters Abstracts International $g 86-02.
790 $a 0132
791 $a M.S.
792 $a 2024
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31485516