rdf-syntax-grammar
mods:
  schema location: http://www.loc.gov/mods/v3 http://www.loc.gov/standards/mods/v3/mods-3-2.xsd
  title info:
    title: Stability of High-Speed, Three-Dimensional Boundary Layers
  name:
    name part: Craig, Stuart A
    role:
      role term: creator
    role:
      role term: author.
  name:
    name part: Saric, W. S.
    role:
      role term: thesis advisor.
  name:
    name part: Texas A & M University
    role:
      role term: degree granting institution.
  type of resource: text
  genre: bibliography
  origin info:
    place:
      place term: txu
    date issued: 2015
    issuance: monographic
  language:
    language term: eng
  physical description:
    form: remote
    extent: 1 online resource.
  abstract: Boundary-layer experiments are performed in the low-disturbance, Mach 6 Quiet Tunnel (M6QT) at Texas A&M University. The experiments are focused specifically on investigating the physics of two three-dimensional phenomena in hypersonic boundary-layer stability and transition: the breakdown of second-mode waves and the growth and breakdown of crossflow waves. In order to enable these experiments, a new, three-dimensional probe traversing mechanism was designed and constructed. In order to investigate the breakdown of second-mode waves, experiments are conducted on a flared cone with a 5° half angle at the tip at zero angle of attack. Experiments were typically performed at unit Reynolds number Re' [approximately equal] 10 x10⁶/m with a slightly hot wall, T/Taw [approximately equal] 1.05. A new, durable method of roughness element application is discussed for the purpose of exciting the unstable waves. Hot-wire measurements were made of the boundary layer and it is shown that even with roughness elements, transition to turbulence does not occur on the model. Therefore, the expected [logical conjunction] vortices are not observed. The crossflow instability in a hypersonic boundary layer is studied on a 7° right circular cone at 5.6° angle of incidence. Experiments were performed at Re' [approximately equal] 10 x10⁶/m with an adiabatic wall. Hot wire measurements are made at a series of axial locations to generate contours of streamwise mass flux. The stationary vortex structure is shown through its saturation. Traveling waves are observed in the expected frequency range, 10 kHz to 60 kHz, predicted by computations and are located generally in the high-speed troughs in the vortex structure. Secondary instability is observed between 80 kHz and 130 kHz. Frequency scaling and location is shown to agree with low-speed experiments and good preliminary agreement with hypersonic computations is obtained. Transition does not naturally occur on the model. Distributed roughness i…
  note: by Stuart A. Craig.
  note: "Major Subject: Aerospace Engineering"
  note: Includes vita.
  note: Doctor of Philosophy Texas A & M University 2015 http://hdl.handle.net/1969.1/155069
  note: Includes bibliographical references.
  note: Text (Dissertation)
  subject:
    topic: Major Aerospace Engineering
  subject:
    topic: boundary layers
  subject:
    topic: laminar-turbulent transition
  subject:
    topic: crossflow
  subject:
    topic: hypersonics
  subject:
    topic: fluid mechanics
  subject:
    topic: aerodynamics
  identifier: http://hdl.handle.net/1969.1/155069
  record info:
    record content source: TXA
    record creation date: 160303
    record change date: 20170928112055.0
    record identifier: in00003609526
    language of cataloging:
      language term: eng