國立虎尾科技大學 |

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

紀錄類型:	書目-語言資料,手稿 : 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.
面頁冊數:	1 online resource (95 pages)
附註:	Source: Masters Abstracts International, Volume: 85-05.
Contained By:	Masters Abstracts International85-05.
標題:	Fluid mechanics. -
電子資源:	click for full text (PQDT)
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. - 1 online resource (95 pages)

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

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

Includes bibliographical references

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.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798380845687Subjects--Topical Terms:

555551
Fluid mechanics.
Subjects--Index Terms:

Boundary layer interactionIndex Terms--Genre/Form:

554714
Electronic books.

Computational Study of Hypersonic Shock Wave Turbulent Boundary Layer Interaction on a Porous Wall.
LDR:03168ntm a22004097 4500 001 1145123
005 20240617111350.5
006 m o d
007 cr mn ---uuuuu
008 250605s2023 xx obm 000 0 eng d
020 $a 9798380845687
035 $a (MiAaPQ)AAI30527397
035 $a AAI30527397
040 $a MiAaPQ $b eng $c MiAaPQ $d NTU
100 1 $a Patel, Raj. $3 1295580
245 1 0 $a Computational Study of Hypersonic Shock Wave Turbulent Boundary Layer Interaction on a Porous Wall.
264 0 $c 2023
300 $a 1 online resource (95 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: 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.
504 $a Includes bibliographical references
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.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2024
538 $a Mode of access: World Wide Web
650 4 $a Fluid mechanics. $3 555551
650 4 $a Engineering. $3 561152
650 4 $a Mechanical engineering. $3 557493
650 4 $a Aerospace engineering. $3 686400
653 $a Boundary layer interaction
653 $a Computation Fluid Dynamics
653 $a Hypersonic vehicles
653 $a Reynolds-Averaged Navier-Stokes
653 $a Turbulent flow
655 7 $a Electronic books. $2 local $3 554714
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 1241251
710 2 $a ProQuest Information and Learning Co. $3 1178819
773 0 $t Masters Abstracts International $g 85-05.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30527397 $z click for full text (PQDT)