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Transonic Limits of Linearized Theory

Cole, J. D. (1954) Transonic Limits of Linearized Theory. California Institute of Technology , Pasadena, CA. (Unpublished)

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The transonic regime, extending from Mach numbers at which shock waves first appear with the associated drag rise to Mach numbers at which the head shock wave is firmly attached to the nose of the body, is well known. Not so well known, perhaps, is the reason for the failure of linearized theory to describe the flow in this regime, in particular, to permit an accurate calculation of the pressure.

Item Type:Report or Paper (Technical Report)
Additional Information:© 1954 California Institute of Technology. OSR Technical Note 228. Contract AF-18(600)-383 Air Research and Development Command.
Group:Graduate Aeronautical Laboratories (Fluid Mechanics), GALCIT
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)AF-18(600)-383
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OSR Technical Note228
Record Number:CaltechAUTHORS:20141114-104653926
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:51766
Deposited On:14 Nov 2014 18:58
Last Modified:22 Nov 2021 18:59

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