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: Developments for a Swept Wing Airfoil to Study the Effects of Step and Gap Excrescences on Boundary Layer Transition
  name:
    name part: Hedderman, Simon Peter
    role:
      role term: creator
    role:
      role term: author.
  name:
    name part: Saric, William
    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: 2013
    issuance: monographic
  language:
    language term: eng
  physical description:
    form: remote
    extent: 1 online resource.
  abstract: Skin friction drag reduction is one of the most promising paths in the investigation of the reduction of aircraft fuel burn. 40 - 50 % of overall drag comes from the surfaces of the wings and stabilizers. Natural laminar flow airfoils can extend the region of laminar flow and reduce skin friction drag. However, real-world aircraft wings do not have perfectly smooth surfaces, and therefore the tolerances for step and gap excrescences on these airfoils must be investigated. Previous work has focused on excrescences on flat plates, and only recently included pressure gradient effects. A new three-dimensional swept wing airfoil with an actuated leading edge (SWIFTER) has been constructed, and will extend the body of knowledge of step and gap excrescences to a more real-world configuration and higher Reynolds numbers. An integrated control system for the leading edge actuation system is proposed, including both interface hardware and control code. A heating system for the test surface is also discussed, and the controller hardware, sensors, and code specified. For wind tunnel testing, a proposed set of wall liners are developed from zero-lift condition streamlines and divided into parts suitable for manufacturing, assembly, and installation. Finally, preliminary wind tunnel step excrescence tests using an existing swept-wing model and applique step material were conducted, and the results are discussed with relevance to testing on the new model. The electronic version of this dissertation is accessible from http://hdl.handle.net/1969.1/149269
  note: by Simon Peter Hedderman.
  note: "Major Subject: Aerospace Engineering"
  note: Includes vita.
  note: Master of Science Texas A & M University 2013 http://hdl.handle.net/1969.1/149269
  note: Includes bibliographical references.
  note: Text (Thesis)
  subject:
    topic: Major Aerospace Engineering
  subject:
    topic: boundary layer
  subject:
    topic: stability
  subject:
    topic: excrescence
  subject:
    topic: excrescences
  subject:
    topic: SWIFT
  subject:
    topic: SWIFTER
  subject:
    topic: step
  subject:
    topic: gap
  subject:
    topic: airfoil
  subject:
    topic: swept wing
  subject:
    topic: actuation control system
  subject:
    topic: heating sheet
  subject:
    topic: wind tunnel
  subject:
    topic: wall liners
  subject:
    topic: natural laminar flow
  subject:
    topic: nlf
  identifier: http://hdl.handle.net/1969.1/149269
  record info:
    record content source: TXA
    record creation date: 140129
    record change date: 20151206091636.0
    record identifier: in00003426824
    language of cataloging:
      language term: eng