NDLI: A finite difference method for predicting supersonic turbulent boundary layer flows with tangential slot injection

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A finite difference method for predicting supersonic turbulent boundary layer flows with tangential slot injection

Content Provider	NASA Technical Reports Server (NTRS)
Author	Miner, E. W. Lewis, C. H.
Copyright Year	1972
Description	An implicit finite difference method has been applied to tangential slot injection into supersonic turbulent boundary layer flows. In addition, the effects induced by the interaction between the boundary layer displacement thickness and the external pressure field are considered. In the present method, three different eddy viscosity models have been used to specify the turbulent momentum exchange. One model depends on the species concentration profile and the species conservation equation has been included in the system of governing partial differential equations. Results are compared with experimental data at stream Mach numbers of 2.4 and 6.0 and with results of another finite difference method. Good agreement was generally obtained for the reduction of wall skin friction with slot injection and with experimental Mach number and pitot pressure profiles. Calculations with the effects of pressure interaction included showed these effects to be smaller than effects of changing eddy viscosity models.
File Size	2717099
Page Count	80
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19720025621
Archival Resource Key	ark:/13960/t9c58cf0t
Language	English
Publisher Date	1972-10-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics Supersonic Flow Slots Finite Difference Theory Turbulent Boundary Layer Mathematical Models Injection Eddy Viscosity Boundary Layer Flow 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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