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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]
상세정보
- 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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■020 ▼a9798380828482
■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
