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Plane Couette Flow at Low Mach Number According to the Kinetic Theory of Gases

Yang, Hsun-Tiao and Lees, Lester (1957) Plane Couette Flow at Low Mach Number According to the Kinetic Theory of Gases. California Institute of Technology , Pasadena, CA. (Unpublished)

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The thirteen-moment approximation developed by H. Grad for solving the Maxwell-Boltzmann equation is applied to the problem of the relative shearing motion between two infinite, parallel flat plates (plane Couette flow). In order to bring out the molecular effects as directly as possible the problem is linearized by requiring that the Mach number is small compared with unity, and that the temperature difference between the two plates is small compared with ambient temperature. According to the linearized Grad equations the shear stress in this case is given by the usual Navier-Stokes relation for all values of the parameter Re/M, in agreement with R. A. Millikan's postulate. Also the linearized boundary conditions for this problem are identical with the Maxwell slip relations utilized by Millikan, so the same expressions for slip velocity and drag coefficient are obtained. An examination of the drag data obtained by Kuhlthau, Chiang, and Bowyer and Talbot in their rotating-cylinder experiments at low densities shows that the variation of 1/C_DM with Re/M is predicted reasonably well by this theory over a range of Mach numbers from 0.15 to 1.40, in spite of the fact that the theory is supposed to hold only for low Mach numbers.

Item Type:Report or Paper (Technical Report)
Additional Information:Hypersonic Research Project Memorandum No. 36 February 1, 1957. Army Ordnance Contract No. DA-04-495-Ord-19 Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE. A portion of this study was completed after Dr. Yang had taken up his new post as Research Associate at the Institute for Fluid Dynamics and Applied Mathematics, University of Maryland. The support of Dr. Yang's work at Maryland by the Office of Scientific Research, Air Research and Development Command, U. S. A. F., under Contract AF 18(600)933, is gratefully acknowledged.
Group:Hypersonic Research Project
Funding AgencyGrant Number
U.S. Army Office of OrdnanceDA-04-495-Ord-19
Air Force Office of Scientific Research (AFOSR)AF 18(600)933
Record Number:CaltechAUTHORS:20150604-152209034
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:58019
Deposited On:05 Jun 2015 03:36
Last Modified:03 Oct 2019 08:31

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