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The Performance of a Supersonic Airplane


Weldon, Thomas Franklin (1947) The Performance of a Supersonic Airplane. Engineer's thesis, California Institute of Technology. doi:10.7907/T271-MK09.


This thesis is primarily a survey of the methods of calculating drag and performance of an airplane capable of supersonic flight. As a basis of presentation of the findings of this survey the drag and performance calculations are worked out for a single place airplane which has a rocket power plant, sweptback wings and other low drag features. These calculations reveal that this airplane should be able to attain a Mach number of 2 at an altitude of 42,000 feet.

Item Type:Thesis (Engineer's thesis)
Subject Keywords:Electrical Engineering
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Electrical Engineering
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Puckett, Allen E.
Thesis Committee:
  • Unknown, Unknown
Defense Date:1947
Record Number:CaltechETD:etd-09142005-112442
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:3531
Deposited By: Imported from ETD-db
Deposited On:14 Sep 2005
Last Modified:16 Mar 2023 22:50

Thesis Files

PDF (Weldon_tf_1947.pdf) - Final Version
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