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Flow Field Around a Finite Cone with Shock


MacKinnon, Neil Allan (1949) Flow Field Around a Finite Cone with Shock. Engineer's thesis, California Institute of Technology. doi:10.7907/XR4M-9R51.


An experimental investigation was made to determine the characteristics of the flow over the surface of a 70° cone and at the shock wave for values near the detachment Mach number. The purpose of this investigation was to compare the experimental results obtained with theoretical values. Tests were made in the GALCIT 2.5" Supersonic Wind Tunnel on a 70° cone at zero angle of attack for five different free stream Mach numbers: 1.49, 1.630, 1.694, 1.86, 1.997. It was found that theory gives close agreement with experimental results. This investigation was conducted jointly with Mr. Vincent Muirhead at the California Institute of Technology, Pasadena, California.

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. (advisor)
  • Nagamatsu, Henry T. (advisor)
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1949
Record Number:CaltechETD:etd-02182009-110248
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:675
Deposited By: Imported from ETD-db
Deposited On:19 Feb 2009
Last Modified:28 Mar 2023 21:43

Thesis Files

PDF (MacKinnon_na_1949.pdf) - Final Version
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