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Characterizing 3D Hypersonic Boundary Layers with Transient Surface Heat Flux Measurements- [electronic resource]
Characterizing 3D Hypersonic Boundary Layers with Transient Surface Heat Flux Measurements- [electronic resource]

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자료유형  
 학위논문
Control Number  
0016935857
International Standard Book Number  
9798380828482
Dewey Decimal Classification Number  
629.1
Main Entry-Personal Name  
Wirth, John M.
Publication, Distribution, etc. (Imprint  
[S.l.] : Texas A&M University., 2023
Publication, Distribution, etc. (Imprint  
Ann Arbor : ProQuest Dissertations & Theses, 2023
Physical Description  
1 online resource(216 p.)
General Note  
Source: Dissertations Abstracts International, Volume: 85-05, Section: B.
General Note  
Advisor: Bowersox, Rodney.
Dissertation Note  
Thesis (Ph.D.)--Texas A&M University, 2023.
Restrictions on Access Note  
This item must not be sold to any third party vendors.
Summary, Etc.  
요약A primary challenge inhibiting hypersonic flight is the inability of current methods to adequately predict the thermal loading in hypersonic flight. Key to solving this problem is understanding the boundary layer around realistic flight geometries, which may have varying properties in all 3 dimensions, and providing databases for testing new models and simulations. This work investigated and provided databases for two geometries of interest to the broader hypersonic research community. The Fin-Cone, which created a 3D boundary layer via fin-induced, shock-boundary layer interactions, was studied with infrared thermography and high-frequency pressure measurements in wind tunnels. A new heat flux analysis was developed incorporating 3D effects to eliminate the uncertainties incurred by lower dimensional methods and provide global heat flux data. The BOLT II, side A flight experiment, which created a 3D boundary layer via highly-swept leading edges and concave surfaces, was analyzed using the 409 channels of temperature, heat flux, pressure, and skin-friction data, taking advantage of the multi-dimensional analyses developed for the Fin-Cone. Transition by at least two mechanisms in three different regions of the surface was observed in flight and turbulent data were gathered up to a vehicle-length Reynolds number of 45 million. Integration of the atmospheric data, ground tests, and various simulations are ongoing. These two experiments provide crucial data that will continue to be leveraged to provide a better understanding of 3D, hypersonic boundary layers.
Subject Added Entry-Topical Term  
Aerospace engineering.
Subject Added Entry-Topical Term  
Applied physics.
Subject Added Entry-Topical Term  
Fluid mechanics.
Index Term-Uncontrolled  
Hypersonic
Index Term-Uncontrolled  
Boundary layer
Index Term-Uncontrolled  
Shock-boundary layer interaction (SBLI)
Added Entry-Corporate Name  
Texas A&M University Aerospace Engineering
Host Item Entry  
Dissertations Abstracts International. 85-05B.
Host Item Entry  
Dissertation Abstract International
Electronic Location and Access  
로그인을 한후 보실 수 있는 자료입니다.
Control Number  
joongbu:642542

MARC

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■035    ▼a(MiAaPQ)AAI30872945
■035    ▼a(MiAaPQ)0803vireo28030Wirth
■040    ▼aMiAaPQ▼cMiAaPQ
■0820  ▼a629.1
■1001  ▼aWirth,  John  M.
■24510▼aCharacterizing  3D  Hypersonic  Boundary  Layers  with  Transient  Surface  Heat  Flux  Measurements▼h[electronic  resource]
■260    ▼a[S.l.]▼bTexas  A&M  University.  ▼c2023
■260  1▼aAnn  Arbor▼bProQuest  Dissertations  &  Theses▼c2023
■300    ▼a1  online  resource(216  p.)
■500    ▼aSource:  Dissertations  Abstracts  International,  Volume:  85-05,  Section:  B.
■500    ▼aAdvisor:  Bowersox,  Rodney.
■5021  ▼aThesis  (Ph.D.)--Texas  A&M  University,  2023.
■506    ▼aThis  item  must  not  be  sold  to  any  third  party  vendors.
■520    ▼aA  primary  challenge  inhibiting  hypersonic  flight  is  the  inability  of  current  methods  to  adequately  predict  the  thermal  loading  in  hypersonic  flight.  Key  to  solving  this  problem  is  understanding  the  boundary  layer  around  realistic  flight  geometries,  which  may  have  varying  properties  in  all  3  dimensions,  and  providing  databases  for  testing  new  models  and  simulations.  This  work  investigated  and  provided  databases  for  two  geometries  of  interest  to  the  broader  hypersonic  research  community.  The  Fin-Cone,  which  created  a  3D  boundary  layer  via  fin-induced,  shock-boundary  layer  interactions,  was  studied  with  infrared  thermography  and  high-frequency  pressure  measurements  in  wind  tunnels.  A  new  heat  flux  analysis  was  developed  incorporating  3D  effects  to  eliminate  the  uncertainties  incurred  by  lower  dimensional  methods  and  provide  global  heat  flux  data.  The  BOLT  II,  side  A  flight  experiment,  which  created  a  3D  boundary  layer  via  highly-swept  leading  edges  and  concave  surfaces,  was  analyzed  using  the  409  channels  of  temperature,  heat  flux,  pressure,  and  skin-friction  data,  taking  advantage  of  the  multi-dimensional  analyses  developed  for  the  Fin-Cone.  Transition  by  at  least  two  mechanisms  in  three  different  regions  of  the  surface  was  observed  in  flight  and  turbulent  data  were  gathered  up  to  a  vehicle-length  Reynolds  number  of  45  million.  Integration  of  the  atmospheric  data,  ground  tests,  and  various  simulations  are  ongoing.  These  two  experiments  provide  crucial  data  that  will  continue  to  be  leveraged  to  provide  a  better  understanding  of  3D,  hypersonic  boundary  layers.
■590    ▼aSchool  code:  0803.
■650  4▼aAerospace  engineering.
■650  4▼aApplied  physics.
■650  4▼aFluid  mechanics.
■653    ▼aHypersonic
■653    ▼aBoundary  layer
■653    ▼aShock-boundary  layer  interaction  (SBLI)
■690    ▼a0538
■690    ▼a0204
■690    ▼a0215
■71020▼aTexas  A&M  University▼bAerospace  Engineering.
■7730  ▼tDissertations  Abstracts  International▼g85-05B.
■773    ▼tDissertation  Abstract  International
■790    ▼a0803
■791    ▼aPh.D.
■792    ▼a2023
■793    ▼aEnglish
■85640▼uhttp://www.riss.kr/pdu/ddodLink.do?id=T16935857▼nKERIS▼z이  자료의  원문은  한국교육학술정보원에서  제공합니다.
■980    ▼a202402▼f2024

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