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Hypersonic Wakes

McCarthy, John F., Jr. (1962) Hypersonic Wakes. Hypersonic Research Project Memorandum, 67. California Institute of Technology , Pasadena, CA. (Unpublished) https://resolver.caltech.edu/CaltechAUTHORS:20151105-161358311

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Abstract

An experimental investigation was made of the flow field behind a two-dimensional circular cylinder at a nominal Mach number of 5.7. The free-stream Reynolds number based on the cylinder diameter was varied over a range from 4300 to 66, 500 by changing both the diameter of the cylinder and the stagnation pressure of the wind tunnel. Pitot-pressure, static-pressure, and total-temperature measurements were made at various distances behind the cylindrical rod in order to determine the state properties in the wake. Base-pressure measurements were also taken at various Reynolds numbers. From these measurements, the transition from laminar to turbulent flow in the wake was determined and successfully correlated with other data. A transition Reynolds number based on local conditions and the length of laminar run was determined. Extensive comparison of the experimental data with Kubota's theory for laminar flow was then made. A satisfactory comparison was made between theory and experiment. Because of the nature of the tests conducted, only a qualitative comparison was made with the theory of Lees and Hromas for turbulent flow.


Item Type:Report or Paper (Technical Report)
Additional Information:Army Ordnance Contract No. DA-04-495-ORD-3231.
Group:Hypersonic Research Project
Funders:
Funding AgencyGrant Number
U. S. Army OrdnanceDA-04-495-ORD-3231
Series Name:Hypersonic Research Project Memorandum
Issue or Number:67
Record Number:CaltechAUTHORS:20151105-161358311
Persistent URL:https://resolver.caltech.edu/CaltechAUTHORS:20151105-161358311
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:61916
Collection:CaltechAUTHORS
Deposited By: Kristin Buxton
Deposited On:06 Nov 2015 00:24
Last Modified:03 Oct 2019 09:13

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