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

On Transonic Wing Shock Unsteadiness.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	On Transonic Wing Shock Unsteadiness./
作者:	Masini, Luke.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2021,
面頁冊數:	161 p.
附註:	Source: Dissertations Abstracts International, Volume: 83-02, Section: B.
Contained By:	Dissertations Abstracts International83-02B.
標題:	Aircraft. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28605671
ISBN:	9798522950163

On Transonic Wing Shock Unsteadiness.
Masini, Luke.

On Transonic Wing Shock Unsteadiness. - Ann Arbor : ProQuest Dissertations & Theses, 2021 - 161 p.

Source: Dissertations Abstracts International, Volume: 83-02, Section: B.

Thesis (Ph.D.)--The University of Liverpool (United Kingdom), 2021.

This item must not be sold to any third party vendors.

Aircraft wings in high-speed flight experience detrimental flow unsteadiness. Its interaction with the flexible wing structure and resulting dynamic loads are addressed in the certification specifications which stipulate a cruise design point free from any structural vibration and buffeting. One such flow unsteadiness is shock buffet and its inherent dynamics near the onset of unsteadiness are addressed herein. Specifically, an extensive experimental dataset of a large aircraft wing geometry and complementary scale-resolving simulations are scrutinised. Whilst the experimental dataset comprises a wide range of flow conditions from pre-onset to established buffet for Mach numbers between 0.70 and 0.84 and four configurations, the primary focus is on the clean wing at the design Mach number of 0.80 and Reynolds number of approximately 3.6 million (based on mean aerodynamic chord). Key to this study are highly-resolved unsteady surface pressure data acquired by dynamic pressure-sensitive paint, in addition to conventional data from pressure transducers and a wing-root strain gauge. To match the experiment and thereby aiding a richer elucidation of the flow physics, detached-eddy simulations are performed using two subgrid length-scale definitions, motivated by the challenge of simulating separating and reattaching shallow shear layers. Modal decomposition techniques are instrumental in pursuing a thorough data analysis. Experimentally, two distinct phenomena in shock-buffet conditions are identified. First, low-frequency shock unsteadiness with characteristic Strouhal numbers between 0.05 and 0.15 (where Strouhal number is based on mean aerodynamic chord and reference freestream velocity) propagates pressure disturbances predominantly inboard. Importantly, this coherent unsteadiness is exclusive to the experiment and even occurs before the strain gauge detects structural buffeting. Second, a broadband higher-frequency behaviour for Strouhal numbers between 0.2 and 0.5 is characterised by three-dimensional cellular patterns describing localised pockets of shear-layer pulsation synchronised with an outboard-propagating shock oscillation. Dominant modal features capturing this characteristic signature show striking similarity between experiment and simulation, detailing the pertinent attributes of shock-buffet unsteadiness whilst contrasting it with the first phenomenon. These findings will help clarify these edge-of-the-envelope flow phenomena and ultimately inform future wing design.

ISBN: 9798522950163Subjects--Topical Terms:

832698
Aircraft.

On Transonic Wing Shock Unsteadiness.
LDR:03732nmm a2200421 4500 001 2347922
005 20220829094951.5
008 241004s2021 ||||||||||||||||| ||eng d
020 $a 9798522950163
035 $a (MiAaPQ)AAI28605671
035 $a (MiAaPQ)Liverpool_3119500
035 $a AAI28605671
040 $a MiAaPQ $c MiAaPQ
100 1 $a Masini, Luke. $3 3687231
245 1 0 $a On Transonic Wing Shock Unsteadiness.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2021
300 $a 161 p.
500 $a Source: Dissertations Abstracts International, Volume: 83-02, Section: B.
500 $a Advisor: Timme, Sebastian;Peace, Andrew J.
502 $a Thesis (Ph.D.)--The University of Liverpool (United Kingdom), 2021.
506 $a This item must not be sold to any third party vendors.
520 $a Aircraft wings in high-speed flight experience detrimental flow unsteadiness. Its interaction with the flexible wing structure and resulting dynamic loads are addressed in the certification specifications which stipulate a cruise design point free from any structural vibration and buffeting. One such flow unsteadiness is shock buffet and its inherent dynamics near the onset of unsteadiness are addressed herein. Specifically, an extensive experimental dataset of a large aircraft wing geometry and complementary scale-resolving simulations are scrutinised. Whilst the experimental dataset comprises a wide range of flow conditions from pre-onset to established buffet for Mach numbers between 0.70 and 0.84 and four configurations, the primary focus is on the clean wing at the design Mach number of 0.80 and Reynolds number of approximately 3.6 million (based on mean aerodynamic chord). Key to this study are highly-resolved unsteady surface pressure data acquired by dynamic pressure-sensitive paint, in addition to conventional data from pressure transducers and a wing-root strain gauge. To match the experiment and thereby aiding a richer elucidation of the flow physics, detached-eddy simulations are performed using two subgrid length-scale definitions, motivated by the challenge of simulating separating and reattaching shallow shear layers. Modal decomposition techniques are instrumental in pursuing a thorough data analysis. Experimentally, two distinct phenomena in shock-buffet conditions are identified. First, low-frequency shock unsteadiness with characteristic Strouhal numbers between 0.05 and 0.15 (where Strouhal number is based on mean aerodynamic chord and reference freestream velocity) propagates pressure disturbances predominantly inboard. Importantly, this coherent unsteadiness is exclusive to the experiment and even occurs before the strain gauge detects structural buffeting. Second, a broadband higher-frequency behaviour for Strouhal numbers between 0.2 and 0.5 is characterised by three-dimensional cellular patterns describing localised pockets of shear-layer pulsation synchronised with an outboard-propagating shock oscillation. Dominant modal features capturing this characteristic signature show striking similarity between experiment and simulation, detailing the pertinent attributes of shock-buffet unsteadiness whilst contrasting it with the first phenomenon. These findings will help clarify these edge-of-the-envelope flow phenomena and ultimately inform future wing design.
590 $a School code: 0722.
650 4 $a Aircraft. $3 832698
650 4 $a Velocity. $3 3560495
650 4 $a Physics. $3 516296
650 4 $a Viscosity. $3 1050706
650 4 $a Vortices. $3 3681507
650 4 $a Turbulence models. $3 3682363
650 4 $a Computer aided design--CAD. $3 3561162
650 4 $a Signal processing. $3 533904
650 4 $a Eigen values. $3 3680699
650 4 $a Decomposition. $3 3561186
650 4 $a Numerical analysis. $3 517751
650 4 $a Pressure distribution. $3 3564852
650 4 $a Reynolds number. $3 3681436
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Applied mathematics. $3 2122814
650 4 $a Design. $3 518875
650 4 $a Engineering. $3 586835
650 4 $a Fluid mechanics. $3 528155
650 4 $a Mathematics. $3 515831
650 4 $a Mechanics. $3 525881
650 4 $a Philosophy. $3 516511
650 4 $a Psychology. $3 519075
650 4 $a Standard deviation. $3 3560390
650 4 $a Simulation. $3 644748
690 $a 0605
690 $a 0538
690 $a 0364
690 $a 0389
690 $a 0537
690 $a 0204
690 $a 0338
690 $a 0405
690 $a 0346
690 $a 0422
690 $a 0621
710 2 $a The University of Liverpool (United Kingdom). $3 1684840
773 0 $t Dissertations Abstracts International $g 83-02B.
790 $a 0722
791 $a Ph.D.
792 $a 2021
793 $a English
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28605671