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Direct and Large-Eddy Simulation Data and Analysis of Shock-Separated Flows.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Direct and Large-Eddy Simulation Data and Analysis of Shock-Separated Flows./
作者:	Helm, Clara M.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2021,
面頁冊數:	188 p.
附註:	Source: Dissertations Abstracts International, Volume: 83-02, Section: B.
Contained By:	Dissertations Abstracts International83-02B.
標題:	Aerospace engineering. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28418599
ISBN:	9798534672237

Direct and Large-Eddy Simulation Data and Analysis of Shock-Separated Flows.
Helm, Clara M.

Direct and Large-Eddy Simulation Data and Analysis of Shock-Separated Flows. - Ann Arbor : ProQuest Dissertations & Theses, 2021 - 188 p.

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

Thesis (Ph.D.)--University of Maryland, College Park, 2021.

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

The in-house CRoCCo code is used to generate a database of high-fidelity direct numerical simulation (DNS) and large eddy simulation (LES) data of shock wave and turbulent boundary layer interactions (STBLI) at supersonic to hypersonic conditions. The DNS data is employed in the validation of the LES method and the assessment of the sub-grid-scale (SGS) models in application to the STBLI flow problem. It is determined that, under hypersonic conditions, a scale similar model term in both the shear stress and heat transfers SGS terms is necessary to produce the correct STBLI separation flow. The use of the dynamic eddy viscosity term alone produced as much as 30% error in separation length. The high grid-resolving efficiency (equivalently the practicality over the DNS) of the CRoCCo code LES method for the simulation of STBLI flows is also demonstrated with a typical reduction of 95% grid size and 67% in number of time steps as compared to the DNS, a feature that makes spectral convergence of the STBLI low-frequency cycle feasible. The thorough documentation of DNS-validated, high-fidelity LES solutions of hypersonic STBLI flows is a unique contribution of this work. Thanks to the detail in the turbulence data afforded by the LES, an extensive and novel characterization of the separation shear layer in the STBLI flows is possible and the results are related to compressible mixing layer theory. In addition, visualizations of the numerical data show the form of the inviscid instability in hypersonic shock-separated flows. These visualizations combined with the extended CRoCCo Lab numerical database provide significant insight into the nature of the separation length scaling in STBLI at hypersonic Mach numbers.

ISBN: 9798534672237Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Boundary layer separation

Direct and Large-Eddy Simulation Data and Analysis of Shock-Separated Flows.
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245 1 0 $a Direct and Large-Eddy Simulation Data and Analysis of Shock-Separated Flows.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2021
300 $a 188 p.
500 $a Source: Dissertations Abstracts International, Volume: 83-02, Section: B.
500 $a Advisor: Martin, M. Pino.
502 $a Thesis (Ph.D.)--University of Maryland, College Park, 2021.
506 $a This item must not be sold to any third party vendors.
520 $a The in-house CRoCCo code is used to generate a database of high-fidelity direct numerical simulation (DNS) and large eddy simulation (LES) data of shock wave and turbulent boundary layer interactions (STBLI) at supersonic to hypersonic conditions. The DNS data is employed in the validation of the LES method and the assessment of the sub-grid-scale (SGS) models in application to the STBLI flow problem. It is determined that, under hypersonic conditions, a scale similar model term in both the shear stress and heat transfers SGS terms is necessary to produce the correct STBLI separation flow. The use of the dynamic eddy viscosity term alone produced as much as 30% error in separation length. The high grid-resolving efficiency (equivalently the practicality over the DNS) of the CRoCCo code LES method for the simulation of STBLI flows is also demonstrated with a typical reduction of 95% grid size and 67% in number of time steps as compared to the DNS, a feature that makes spectral convergence of the STBLI low-frequency cycle feasible. The thorough documentation of DNS-validated, high-fidelity LES solutions of hypersonic STBLI flows is a unique contribution of this work. Thanks to the detail in the turbulence data afforded by the LES, an extensive and novel characterization of the separation shear layer in the STBLI flows is possible and the results are related to compressible mixing layer theory. In addition, visualizations of the numerical data show the form of the inviscid instability in hypersonic shock-separated flows. These visualizations combined with the extended CRoCCo Lab numerical database provide significant insight into the nature of the separation length scaling in STBLI at hypersonic Mach numbers.
590 $a School code: 0117.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Fluid mechanics. $3 528155
650 4 $a Computational physics. $3 3343998
650 4 $a Friction. $3 650299
650 4 $a Heat transfer. $3 3391367
650 4 $a Simulation. $3 644748
650 4 $a Velocity. $3 3560495
650 4 $a Accuracy. $3 3559958
650 4 $a Physics. $3 516296
650 4 $a Datasets. $3 3541416
650 4 $a Viscosity. $3 1050706
650 4 $a Vortices. $3 3681507
650 4 $a Turbulence models. $3 3682363
650 4 $a Sensors. $3 3549539
650 4 $a Methods. $3 3560391
650 4 $a Energy. $3 876794
650 4 $a Reynolds number. $3 3681436
650 4 $a Visualization. $3 586179
653 $a Boundary layer separation
653 $a Compressible flows
653 $a Shock waves
653 $a Turbulent flows
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690 $a 0204
690 $a 0216
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791 $a Ph.D.
792 $a 2021
793 $a English
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