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Electric analog computer study of supersonic flutter of elastic delta wings

Citation

Basin, Michael A. (1954) Electric analog computer study of supersonic flutter of elastic delta wings. Dissertation (Ph.D.), California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-11252003-111202

Abstract

This thesis presents a method for the solution of the supersonic flutter problem for elastic delta wings with supersonic leading edges.

In Part I, the necessary aerodynamic equations are developed, first in integral form, and then in a power series expansion in order to obtain a practical expression for the pressure at a point on the wing due to the motion of the wing surface in a supersonic air stream.

Part II gives a method for computing the lifts on a partitioned wing, and sets up cell division criteria. These methods are then applied to a specific wing form.

Parts III and IV present the electrical analogs for the aerodynamic lifts, and for the elastic wing structure respectively. These analogs are then applied to the example of part II.

Part V presents the results of the actual flutter study performed on the above wing on the California Institute of Technology Electric Analog Computer.

Part VI contains the conclusions of the study, and recommendations and suggestions for further research.

Item Type:Thesis (Dissertation (Ph.D.))
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Engineering and Applied Science
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • McCann, Gilbert Donald (advisor)
  • Wilts, Charles H. (co-advisor)
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1954
Record Number:CaltechETD:etd-11252003-111202
Persistent URL:http://resolver.caltech.edu/CaltechETD:etd-11252003-111202
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:4659
Collection:CaltechTHESIS
Deposited By: Imported from ETD-db
Deposited On:26 Nov 2003
Last Modified:26 Dec 2012 03:10

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