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Computational Study of Hypersonic Sh...

Patel, Raj.

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Computational Study of Hypersonic Shock Wave Turbulent Boundary Layer Interaction on a Porous Wall.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Computational Study of Hypersonic Shock Wave Turbulent Boundary Layer Interaction on a Porous Wall./
作者:	Patel, Raj.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2023,
面頁冊數:	95 p.
附註:	Source: Masters Abstracts International, Volume: 85-05.
Contained By:	Masters Abstracts International85-05.
標題:	Aerospace engineering. -
電子資源:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30527397
ISBN:	9798380845687

Computational Study of Hypersonic Shock Wave Turbulent Boundary Layer Interaction on a Porous Wall.
Patel, Raj.

Computational Study of Hypersonic Shock Wave Turbulent Boundary Layer Interaction on a Porous Wall. - Ann Arbor : ProQuest Dissertations & Theses, 2023 - 95 p.

Source: Masters Abstracts International, Volume: 85-05.

Thesis (M.S.)--Rutgers The State University of New Jersey, School of Graduate Studies, 2023.

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

The shock wave turbulent boundary layer interaction (STBLI) phenomenon has been actively researched in the last five decades. These interactions usually occur in hypersonic vehicles, where the shock generated from control surfaces interacts with the attached boundary layer. Designing hypersonic vehicles requires a tool to predict the aerothermodynamic loads, which can be done by performing Computation Fluid Dynamics (CFD) simulations. Reynolds-Averaged Navier-Stokes (RANS) simulations have been extensively used to predict the turbulent flow behavior, which utilizes the turbulence model to solve the nonlinear RANS equations. This computational study comprises two-dimensional RANS simulations of the interaction of incident shock waves with a turbulent boundary layer at Mach 6 in the presence of surface blowing. A couple of cases were computed, one without the surface blowing and the other with the presence of surface blowing. The computed results of surface heat transfer and pressure are compared with the experimental study done at the Calspan University at Buffalo Research Center (CUBRC). For this thesis, the k − ω and k − ϵ turbulence models were utilized to predict the surface heat transfer and pressure. The results show that both models predict the peak pressure values with experimental uncertainty in both cases. The k − ϵ model predicts the peak heat transfer with reasonable error in both cases. The k − ω model underpredicted the peak heat transfer in the case without surface blowing and gave anomalous results in predicting surface heat transfer over a porous plate. However, both turbulence models have proven to be poor predictors in the STBLI region.

ISBN: 9798380845687Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Boundary layer interaction

Computational Study of Hypersonic Shock Wave Turbulent Boundary Layer Interaction on a Porous Wall.
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100 1 $a Patel, Raj. $3 874476
245 1 0 $a Computational Study of Hypersonic Shock Wave Turbulent Boundary Layer Interaction on a Porous Wall.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2023
300 $a 95 p.
500 $a Source: Masters Abstracts International, Volume: 85-05.
500 $a Advisor: Knight, Doyle.
502 $a Thesis (M.S.)--Rutgers The State University of New Jersey, School of Graduate Studies, 2023.
506 $a This item must not be sold to any third party vendors.
520 $a The shock wave turbulent boundary layer interaction (STBLI) phenomenon has been actively researched in the last five decades. These interactions usually occur in hypersonic vehicles, where the shock generated from control surfaces interacts with the attached boundary layer. Designing hypersonic vehicles requires a tool to predict the aerothermodynamic loads, which can be done by performing Computation Fluid Dynamics (CFD) simulations. Reynolds-Averaged Navier-Stokes (RANS) simulations have been extensively used to predict the turbulent flow behavior, which utilizes the turbulence model to solve the nonlinear RANS equations. This computational study comprises two-dimensional RANS simulations of the interaction of incident shock waves with a turbulent boundary layer at Mach 6 in the presence of surface blowing. A couple of cases were computed, one without the surface blowing and the other with the presence of surface blowing. The computed results of surface heat transfer and pressure are compared with the experimental study done at the Calspan University at Buffalo Research Center (CUBRC). For this thesis, the k − ω and k − ϵ turbulence models were utilized to predict the surface heat transfer and pressure. The results show that both models predict the peak pressure values with experimental uncertainty in both cases. The k − ϵ model predicts the peak heat transfer with reasonable error in both cases. The k − ω model underpredicted the peak heat transfer in the case without surface blowing and gave anomalous results in predicting surface heat transfer over a porous plate. However, both turbulence models have proven to be poor predictors in the STBLI region.
590 $a School code: 0190.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Mechanical engineering. $3 649730
650 4 $a Engineering. $3 586835
650 4 $a Fluid mechanics. $3 528155
653 $a Boundary layer interaction
653 $a Computation Fluid Dynamics
653 $a Hypersonic vehicles
653 $a Reynolds-Averaged Navier-Stokes
653 $a Turbulent flow
690 $a 0538
690 $a 0548
690 $a 0537
690 $a 0204
710 2 $a Rutgers The State University of New Jersey, School of Graduate Studies. $b Mechanical and Aerospace Engineering. $3 3435840
773 0 $t Masters Abstracts International $g 85-05.
790 $a 0190
791 $a M.S.
792 $a 2023
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30527397