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DSMC Computations for Regions of Shock/Shock and Shock/Boundary Layer InteractionThis 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.
Document ID
20010014197
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Moss, James N. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
January 11, 2001
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2001-1027
Meeting Information
Meeting: Aerospace Sciences
Location: Reno, NV
Country: United States
Start Date: January 8, 2001
End Date: January 11, 2001
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.

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