CaltechTHESIS
  A Caltech Library Service

Flow field and stability of the far wake behind cylinders at hypersonic speeds

Citation

Behrens, Wilhelm (1966) Flow field and stability of the far wake behind cylinders at hypersonic speeds. Dissertation (Ph.D.), California Institute of Technology. http://resolver.caltech.edu/CaltechTHESIS:08172010-151639253

Abstract

An experimental study of the mean wake flow field and its stability has been carried out in the far wake of circular cylinders at a Mach number of 6. The Reynolds numbers ranged from 200 to 4000 with a few measurements at higher Reynolds number. Pitot pressure, static pressure and mean flow hot wire measurements were done at many axial stations behind cylinders up to (x/d) = 2400. The inner wake formed from the cylinder boundary layers is laminar and loses its identity within the first 60 diameters or less depending on the Reynolds numbers so that only the outer wake, caused by the bow shock, has to be considered. Within a certain region the experimental results compare well with linear laminar theory, but the wake profiles are not similar up to the farthest downstream station (x/d = 2400). At four Reynolds numbers strong deviations from steady laminar behavior were observed far behind the cylinder, indicating breakdown of the flow because of non-linear instability effects. In the instability study hot wire fluctuation measurements were made over the whole frequency range (f = 1 - 320 KC) and also at particular frequencies in a band width of 1 KC up to x/d = 12000 at the lowest Reynolds number. Two instability regions were found and investigated: the linear growth region and the non-linear region. In the linear region there is quite a close correspondence with linear stability theory. The onset of non-linearity is characterized by the simultaneous strong deviation of the mean flow from laminar steady behavior, the increase of the fundamental frequency fluctuation component on the wake axis and the sudden rise of the first harmonic frequency component. The non-linear region is compared with the non-linear wake region at low speeds behind a flat plate. On the basis of these measurements a tentative picture is given of the onset of non-linearity and/or transition in the inner and outer wake behind blunt bodies at hypersonic speeds.

Item Type:Thesis (Dissertation (Ph.D.))
Subject Keywords:Aeronautics
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Lees, Lester (advisor)
  • Kubota, Toshi (advisor)
Thesis Committee:
  • Unknown, Unknown
Defense Date:12 May 1966
Record Number:CaltechTHESIS:08172010-151639253
Persistent URL:http://resolver.caltech.edu/CaltechTHESIS:08172010-151639253
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:5992
Collection:CaltechTHESIS
Deposited By: Benjamin Perez
Deposited On:18 Aug 2010 14:54
Last Modified:29 Jul 2014 21:20

Thesis Files

[img]
Preview
PDF - Final Version
See Usage Policy.

3946Kb

Repository Staff Only: item control page