NDLI: Relaxation of an unsteady turbulent boundary layer on a flat plate in an expansion tube

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Relaxation of an unsteady turbulent boundary layer on a flat plate in an expansion tube

Content Provider	NASA Technical Reports Server (NTRS)
Author	Gurta, R. N. Trimpi, R. L.
Copyright Year	1974
Description	An analysis is presented for the relaxation of a turbulent boundary layer on a semi-infinite flat plate after passage of a shock wave and a trailing driver gas-driven gas interface. The problem has special application to expansion-tube flows. The flow-governing equations have been transformed into the Crocco variables, and a time-similar solution is presented in terms of the dimensionless distance-time variable alpha and the dimensionless velocity variable beta. An eddy-viscosity model, similar to that of time-steady boundary layers, is applied to the inner and outer regions of the boundary layer. A turbulent Prandtl number equal to the molecular Prandtl number is used to relate the turbulent heat flux to the eddy viscosity. The numerical results, obtained by using the Gauss-Seidel line-relaxation method, indicate that a fully turbulent boundary layer relaxes faster to the final steady-state values of heat transfer and skin friction than a laminar boundary layer. The results also give a fairly good estimate of the local skin friction and heat transfer for near steady-flow conditions.
File Size	988829
Page Count	58
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19740017695
Archival Resource Key	ark:/13960/t9f52fd5z
Language	English
Publisher Date	1974-06-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics Shock Waves Flat Plates Skin Friction Unsteady State Turbulent Boundary Layer Shock Tubes Eddy Viscosity Crocco Method Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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