NDLI: Dsmc simulations of hypersonic flows with shock interactions and validation with experiments

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Dsmc simulations of hypersonic flows with shock interactions and validation with experiments

Content Provider	NASA Technical Reports Server (NTRS)
Author	Bird, Graeme A. Moss, James N.
Copyright Year	2004
Description	The capabilities of a relatively new direct simulation Monte Carlo (DSMC) code are examined for the problem of hypersonic laminar shock/shock and shock/boundary layer interactions, where boundary layer separation is an important feature of the flow. Flow about two model configurations is considered, where both configurations (a biconic and a hollow cylinder-flare) have recent published experimental measurements. The computations are made by using the DS2V code of Bird, a general two-dimensional/axisymmetric time accurate code that incorporates many of the advances in DSMC over the past decade. The current focus is on flows produced in ground-based facilities at Mach 12 and 16 test conditions with nitrogen as the test gas and the test models at zero incidence. Results presented highlight the sensitivity of the calculations to grid resolutions, sensitivity to physical modeling parameters, and comparison with experimental measurements. Information is provided concerning the flow structure and surface results for the extent of separation, heating, pressure, and skin friction.
File Size	5540253
Page Count	14
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20040082220
Archival Resource Key	ark:/13960/t7rn8455f
Language	English
Publisher Date	2004-06-25
Access Restriction	Open
Subject Keyword	Aerodynamics Boundary Layer Separation Shock Layers Sensitivity Simulation Shock Wave Interaction Hypersonic Flow Computerized Simulation Nitrogen Monte Carlo Method Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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