• Refine Query
  • Source
  • Publication year
  • to
  • Language
  • 157
  • 32
  • 14
  • 14
  • 7
  • 5
  • 5
  • 5
  • 5
  • 5
  • 5
  • 3
  • 2
  • 1
  • Tagged with
  • 304
  • 304
  • 85
  • 84
  • 79
  • 54
  • 52
  • 49
  • 43
  • 40
  • 35
  • 32
  • 29
  • 27
  • 24
  • About
  • The Global ETD Search service is a free service for researchers to find electronic theses and dissertations. This service is provided by the Networked Digital Library of Theses and Dissertations.
    Our metadata is collected from universities around the world. If you manage a university/consortium/country archive and want to be added, details can be found on the NDLTD website.
21

Compressible turbulence in a high-speed high Reynolds number mixing layer /

Bowersox, Rodney Dale Welch, January 1992 (has links)
Thesis (Ph. D.)--Virginia Polytechnic Institute and State University, 1992. / Vita. Abstract. Includes bibliographical references (leaves 75-79). Also available via the Internet.
22

Barnacle feeding : comparing cirral anatomy, feeding behavior, Reynolds numbers, and cirral fan leakiness across three size classes of three species of common acorn barnacles /

Geierman, Christina, January 2007 (has links)
Thesis (M.S.)--University of Oregon, 2007. / Typescript. Includes vita and abstract. Includes bibliographical references (leaves 89-97). Also available online.
23

Reynolds stress measurements in a turbine tip leakage vortex /

Heckel, Scott P., January 1992 (has links)
Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1992. / Vita. Abstract. Includes bibliographical references (leaf 109). Also available via the Internet.
24

High Reynolds number simulation and drag reduction techniques : a thesis /

Xu, Jin. January 2005 (has links)
Thesis (Ph.D.)--Brown University, 2005. / Vita. Thesis advisor: G. E. Karniadakis, M. R. Maxey. Includes bibliographical references (leaves 241-253). Also available online.
25

Experimental study of hypersonic boundary layers and base flows

Denman, Paul Ashley January 1996 (has links)
This experimental study documents the development and separation of a hypersonic boundary layer produced naturally on the cold surface of a sharp slender cone. At the base of the conical forebody, the equilibrium turbulent boundary layer was allowed to separate over an axisymmetric rearward facing step to form a compressible base flow. The investigation was conducted in the Imperial College No.2 gun tunnel at a freestream Mach number of 9 and unit Reynolds numbers of 15 and 55 million. The compressible boundary layer study was carried out at both of the available freestream unit Reynolds numbers and the measured data include distributions of wall static pressure and heat transfer rate, together with profiles of pitot pressure through the boundary layer. Using the chordwise distribution of surface heat flux as a means of transition detection, the cone transition Reynolds number was found to be 5.4x10^. This result, together with that obtained from flat plate studies conducted in the same test facility, provided a ratio of cone to flat plate transition Reynolds number of 0.8. Boundary layer integral quantities and shape factors are derived from velocity profiles and in most cases the measured data extended close enough to the wall to detect the peak values of the integrands. The separated flow region formed at the base of the cone was documented only at the higher unit Reynolds number, a condition under which the approaching turbulent boundary layer was found to be close to equilibrium. The data include pitot pressure profiles recorded normal to the surface downstream of reattachment, together with wall static pressure and heat transfer rate distributions measured throughout the base flow region. Reattachment occurred approximately two step heights downstream of separation and a surface flow visualisation study indicated the existence of Taylor-Goertler type vortices, emanating from the reattachment line in the downstream direction. A simple shear layer expansion model is developed and shown to provide a favourable prediction of the measured pitot pressure profiles recorded downstream of the reattachment line. The success of this second order model implies that the dynamics of the corner expansion process, except in the immediate vicinity of the wall, is governed largely by inviscid pressure mechanisms and that the supersonic region of the boundary layer expansion is essentially isentropic.
26

The effect of heat current modulation on the velocity fields and the critical Reynolds number in helium II /

Oberly, Charles Evan January 1971 (has links)
No description available.
27

An investigation of three-dimensional shockwave/turbulent-boundary layer interaction

Leung, Andrew Wing Che January 1993 (has links)
No description available.
28

Lift distributions on low aspect ratio wings at low Reynolds numbers

Sathaye, Sagar Sanjeev. January 2004 (has links)
Thesis (M.S.)--Worcester Polytechnic Institute. / Keywords: Low Reynolds Number; Micro Air Vehicle; Low Aspect Ratio; Spanwise pressure measurements; Spanwise Lift Distributions. Includes bibliographical references (p. 84-85).
29

Low Reynolds number water flow characteristics through rectangular micro diffusers/nozzles with a primary focus on major/minor pressure loss, static pressure recovery and flow separation

Hallenbeck, Kyle J. January 2008 (has links)
Thesis (M.S.)--University of Central Florida, 2008. / Adviser: Larry Chew. Includes bibliographical references (p. 146-148).
30

An experimental investigation of laminar and turbulent mixing of compressible jets at low reynolds numbers

Jensen, Dale Edward 05 1900 (has links)
No description available.

Page generated in 0.0484 seconds