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The downwash distribution behind a delta wing at supersonic speeds


Palmer, George M. (1948) The downwash distribution behind a delta wing at supersonic speeds. Engineer's thesis, California Institute of Technology.


At the present date, very little information exists as to the downwash and sidewash in the wake of lifting surfaces for supersonic missiles and airplanes. To the author's knowledge, Reference 1 is the first paper to develop the theory and carry out numerical calculations for the downwash and sidewash behind wings of practical interest. However, the paper only contained brief indications of how to treat the very interesting triangular planform known as the delta wing.

It is the purpose of this paper to extend the basic idea for the determination of downwash as used in Reference 1, to the delta wing, and to carry out numerical calculations for a specific case. Although it is possible to develop expressions for the downwash and the sidewash at all points within the Mach cone and in the wake of the wing, see Reference 1, it was not carried out here. This paper applies only to the downwash field in the plane of the wing. Another restriction is that the delta wing half angle be less than the Mach angle.

Item Type:Thesis (Engineer's thesis)
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Lagerstrom, Paco A.
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 June 1947
Record Number:CaltechETD:etd-12082008-081222
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:4873
Deposited By: Imported from ETD-db
Deposited On:22 Dec 2008
Last Modified:26 Dec 2012 03:12

Thesis Files

PDF (Palmer_gm_1947.pdf) - Final Version
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