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Application of a transitional boundary-layer theory in the low hypersonic Mach number regimeAn investigation is made to assess the capability of a finite-difference boundary-layer procedure to predict the mean profile development across a transition from laminar to turbulent flow in the low hypersonic Mach-number regime. The boundary-layer procedure uses an integral form of the turbulence kinetic-energy equation to govern the development of the Reynolds apparent shear stress. The present investigation shows the ability of this procedure to predict Stanton number, velocity profiles, and density profiles through the transition region and, in addition, to predict the effect of wall cooling and Mach number on transition Reynolds number. The contribution of the pressure-dilatation term to the energy balance is examined and it is suggested that transition can be initiated by the direct absorption of acoustic energy even if only a small amount (1 per cent) of the incident acoustic energy is absorbed.
Document ID
19750062068
Document Type
Reprint (Version printed in journal)
Authors
Shamroth, S. J.
Mcdonald, H. (United Aircraft Research Laboratories East Hartford, Conn., United States)
Date Acquired
August 8, 2013
Publication Date
November 1, 1975
Publication Information
Publication: International Journal of Heat and Mass Transfer
Volume: 18
Subject Category
AERODYNAMICS
Funding Number(s)
CONTRACT_GRANT: NAS1-10865
Distribution Limits
Public
Copyright
Other