東華大學圖書館 |

語系: 繁體中文

說明(常見問題)

回圖書館首頁

手機版館藏查詢

登入

回首頁

切換: 標籤 | MARC模式 | ISBD

FindBook

Google Book

Amazon

博客來

Exploring Passive Flow Control Techniques Applied to a Supersonic Multistream Rectangular Nozzle.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Exploring Passive Flow Control Techniques Applied to a Supersonic Multistream Rectangular Nozzle./
作者:	Gist, Emma D.
面頁冊數:	1 online resource (167 pages)
附註:	Source: Dissertations Abstracts International, Volume: 84-03, Section: B.
Contained By:	Dissertations Abstracts International84-03B.
標題:	Mechanical engineering. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29209779click for full text (PQDT)
ISBN:	9798841731856

Exploring Passive Flow Control Techniques Applied to a Supersonic Multistream Rectangular Nozzle.
Gist, Emma D.

Exploring Passive Flow Control Techniques Applied to a Supersonic Multistream Rectangular Nozzle. - 1 online resource (167 pages)

Source: Dissertations Abstracts International, Volume: 84-03, Section: B.

Thesis (Ph.D.)--Syracuse University, 2022.

Includes bibliographical references

Passive control techniques are applied experimentally to examine different aspects of a supersonic multistream rectangular nozzle representing a modern airframe-integrated variable cycle engine. The flow is comprised of a core stream (M = 1.6) and bypass (M = 1.0) that merge behind a splitter plate and exit through a Single Expansion Ramp Nozzle (SERN) onto an aft-deck. Previous efforts for the nominal nozzle configuration have shown that an instability initiated at the splitter plate trailing edge (SPTE) influences the effectiveness of the third stream as a barrier for the aft-deck and persists through the entire domain due to its reaction with the shock train. To address this, passive flow control was implemented by introducing sinusoidal spanwise modifications along the splitter plate edge. The SPTE was identified as the highest region of sensitivity via LES. Results on different spanwise wavenumbers indicate reduction of the dominating tone with increasing wavenumber. Additionally, the sinusoidal trailing edge induces streamwise vorticity, which enhances mixing between the two streams and breaks up the shed structures seen previously. A wavenumber corresponding to one simulated was tested experimentally via the use of simultaneous nearfield pressure and velocity in conjunction with farfield acoustics. Farfield acoustic measurements have confirmed the diminishment of the tone for the wavy SPTE. PIV and velocity profiles for mean fields revealed higher plume vectoring for the nominal aft-deck. The shear layers and the region along the aft-deck surface displayed significant enhancement of velocity variability through low order statistics. As a result of this increase, the POD modes were reordered for the wavy SPTE. Wavy modes had smaller spatial structures presented in lower modes, with increased energy content when compared to the same modes in the nominal flow.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2023

Mode of access: World Wide Web

ISBN: 9798841731856Subjects--Topical Terms:

649730
Mechanical engineering.
Subjects--Index Terms:

Flow controlIndex Terms--Genre/Form:

542853
Electronic books.

Exploring Passive Flow Control Techniques Applied to a Supersonic Multistream Rectangular Nozzle.
LDR:03238nmm a2200385K 4500 001 2354439
005 20230414084757.5
006 m o d
007 cr mn ---uuuuu
008 241011s2022 xx obm 000 0 eng d
020 $a 9798841731856
035 $a (MiAaPQ)AAI29209779
035 $a AAI29209779
040 $a MiAaPQ $b eng $c MiAaPQ $d NTU
100 1 $a Gist, Emma D. $3 3694791
245 1 0 $a Exploring Passive Flow Control Techniques Applied to a Supersonic Multistream Rectangular Nozzle.
264 0 $c 2022
300 $a 1 online resource (167 pages)
336 $a text $b txt $2 rdacontent
337 $a computer $b c $2 rdamedia
338 $a online resource $b cr $2 rdacarrier
500 $a Source: Dissertations Abstracts International, Volume: 84-03, Section: B.
500 $a Advisor: Glauser, Mark.
502 $a Thesis (Ph.D.)--Syracuse University, 2022.
504 $a Includes bibliographical references
520 $a Passive control techniques are applied experimentally to examine different aspects of a supersonic multistream rectangular nozzle representing a modern airframe-integrated variable cycle engine. The flow is comprised of a core stream (M = 1.6) and bypass (M = 1.0) that merge behind a splitter plate and exit through a Single Expansion Ramp Nozzle (SERN) onto an aft-deck. Previous efforts for the nominal nozzle configuration have shown that an instability initiated at the splitter plate trailing edge (SPTE) influences the effectiveness of the third stream as a barrier for the aft-deck and persists through the entire domain due to its reaction with the shock train. To address this, passive flow control was implemented by introducing sinusoidal spanwise modifications along the splitter plate edge. The SPTE was identified as the highest region of sensitivity via LES. Results on different spanwise wavenumbers indicate reduction of the dominating tone with increasing wavenumber. Additionally, the sinusoidal trailing edge induces streamwise vorticity, which enhances mixing between the two streams and breaks up the shed structures seen previously. A wavenumber corresponding to one simulated was tested experimentally via the use of simultaneous nearfield pressure and velocity in conjunction with farfield acoustics. Farfield acoustic measurements have confirmed the diminishment of the tone for the wavy SPTE. PIV and velocity profiles for mean fields revealed higher plume vectoring for the nominal aft-deck. The shear layers and the region along the aft-deck surface displayed significant enhancement of velocity variability through low order statistics. As a result of this increase, the POD modes were reordered for the wavy SPTE. Wavy modes had smaller spatial structures presented in lower modes, with increased energy content when compared to the same modes in the nominal flow.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2023
538 $a Mode of access: World Wide Web
650 4 $a Mechanical engineering. $3 649730
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Fluid mechanics. $3 528155
653 $a Flow control
653 $a Multistream
653 $a Rectangular jet
653 $a Supersonic
655 7 $a Electronic books. $2 lcsh $3 542853
690 $a 0548
690 $a 0538
690 $a 0204
710 2 $a ProQuest Information and Learning Co. $3 783688
710 2 $a Syracuse University. $b Mechanical and Aerospace Engineering. $3 2104096
773 0 $t Dissertations Abstracts International $g 84-03B.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29209779 $z click for full text (PQDT)