NDLI: Dsmc computations for regions of shock/shock and shock/boundary layer interaction (Document No: 20010014197)

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Dsmc computations for regions of shock/shock and shock/boundary layer interaction (Document No: 20010014197)

Content Provider	NASA Technical Reports Server (NTRS)
Author	Moss, James N.
Copyright Year	2001
Description	This paper presents the results of a numerical study of hypersonic interacting flows at flow conditions that include those for which experiments have been conducted in the Calspan-University of Buffalo Research Center (CUBRC) Large Energy National Shock (LENS) tunnel and the ONERA R5Ch low-density wind tunnel. The computations are made with the direct simulation Monte Carlo (DSMC) method of Bird. The focus is on Mach 9.3 to 11.4 flows about flared axisymmetric configurations, both hollow cylinder flares and double cones. The results presented highlight the sensitivity of the calculations to grid resolution, provide results concerning the conditions for incipient separation, and provide information concerning the flow structure and surface results for the extent of separation, heating, pressure, and skin friction.
File Size	1761320
Page Count	32
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20010014197
Archival Resource Key	ark:/13960/t17m5759t
Language	English
Publisher Date	2001-01-11
Access Restriction	Open
Subject Keyword	Fluid Mechanics And Thermodynamics Sensitivity Low Density Wind Tunnels Hypersonic Flow Experimentation Computerized Simulation Monte Carlo Method Boundary Layers Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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