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Supersonic Flow in a Two-Dimensional Asymmetric Channel


Benezra, Joseph Nissim (1949) Supersonic Flow in a Two-Dimensional Asymmetric Channel. Engineer's thesis, California Institute of Technology. doi:10.7907/GYFS-PN59.


A practical method is developed whereby the flow field in a two-dimensional asymmetric channel can easily be determined employing the method of characteristics. Some insight as to the accuracy of such a graphical solution is gained by checking against a known theoretical solution. An asymmetric channel having a simple geometric form is designed for uniform exit flow. The lower wall is then shifted various distances to achieve different mean flows at the exit thus simulating the operation of a wind tunnel. The velocity and flow inclination gradients are determined in the test section. The same analysis is performed on a similar channel but with one of the geometric parameters of the throat changed. Finally, an investigation is carried out to determine the amount that the profile of the upper wall differs from what it should be to attain uniform flow in the test section for the various configurations.

Item Type:Thesis (Engineer's thesis)
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):
  • Puckett, Allen E.
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1949
Record Number:CaltechETD:etd-02102009-091251
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:598
Deposited By: Imported from ETD-db
Deposited On:12 Feb 2009
Last Modified:27 Mar 2023 22:44

Thesis Files

PDF (Benezra_jn_1949.pdf) - Final Version
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