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: Characterization of the influence of a favorable pressure gradient on the basic structure of a Mach 5.0 high Reynolds number supersonic turbulent boundary layer
  name:
    name part: Tichenor, Nathan R.
    role:
      role term: creator
  name:
    name part: Bowersox, Rodney D. W.
    role:
      role term: thesis advisor.
  type of resource: text
  genre: bibliography
  origin info:
    place:
      place term: txu
    date issued: 2010
    issuance: monographic
  language:
    language term: eng
  physical description:
    form: remote
    extent: 1 online resource.
  abstract: High-speed high Reynolds number boundary layer flows with mechanical non-equilibrium effects have numerous practical applications; examples include access-to-space ascent, re-entry and descent, and military hypersonic systems. However, many of the basic turbulent flow processes in this regime are poorly understood and are beyond the realm of modern direct numerical simulations Previous studies have shown that curvature driven pressure gradients significantly alter the state of the turbulence in high-speed boundary layers; the turbulence levels have been shown to decrease by large amounts (up to 100 percent) and the Reynolds shear stress has been shown to change sign. However, most of our understanding is based on point measurement techniques such as hot-wire and Laser Doppler anemometry acquired at low to moderate supersonic Mach numbers (i.e., M = 2-3). After reviewing the available literature, the following scientific questions remain unanswered pertaining to the effect of favorable pressure gradients: (1) How is state of the mean flow and turbulence statistics altered? (2) How is the structure of wall turbulence; break-up, stretch or a combination? (3) How are the Reynolds stress component production mechanisms altered? (4) What is the effect of Mach number on the above processes? To answer these questions and to enhance the current database, an experimental analysis was performed to provide high fidelity documentation of the mean and turbulent flow properties using two-dimensional particle image velocimetry (PIV) along with flow visualizations of a high speed (M4.88=), high Reynolds number (Re[is almost equal to]36,000) supersonic turbulent boundary layer with curvature-driven favorable pressure gradients (a nominally zero, a weak, and a strong favorable pressure gradient). From these data, detailed turbulence analyses were performed including calculating classical mean flow and turbulence statistics, examining turbulent stress production, and performing quadran…
  note: by Nathan R. Tichenor.
  note: "Major Subject: Aerospace Engineering"
  note: Title from author supplied metadata (automated record created 2010-11-11 10:17:47).
  note: Electronic resource.
  note: Doctor of Philosophy Texas A&M University 2010 http://hdl.handle.net/1969.1/ETD-TAMU-2010-08-8407
  note: Includes bibliographical references.
  note: Text (Dissertation)
  subject:
    topic: Major Aerospace Engineering
  subject:
    topic: Mach 5.0
  subject:
    topic: favorable pressure gradient
  subject:
    topic: hypersonic
  identifier: http://hdl.handle.net/1969.1/ETD-TAMU-2010-08-8407
  record info:
    record content source: TXA
    record creation date: 101201
    record change date: 20151202112937.0
    record identifier: in00002673670