NDLI: Use of a hyperbolic grid generation scheme in simulating supersonic viscous flow about three-dimensional winged configuration

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Use of a hyperbolic grid generation scheme in simulating supersonic viscous flow about three-dimensional winged configuration

Content Provider	NASA Technical Reports Server (NTRS)
Author	Rizk, Y. M. Steger, J. L. Chaussee, D. S.
Copyright Year	1985
Description	The present paper describes a numerical mesh generation technique to be used with an implicit finite difference method for simulating visous supersonic flow about low-aspect-ratio wing body configurations using a single grid strategy. The computational domain is segmented into multiple regions, with borders located in supersonic areas to avoid the otherwise costly interfacing procedure between adjacent segments. The numerical procedure is applied to calculate the turbulent flow around the shuttle orbiter and a canard projectile at supersonic free stream Mach number.
File Size	776632
Page Count	17
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19850025803
Archival Resource Key	ark:/13960/t8nd0v068
Language	English
Publisher Date	1985-07-01
Access Restriction	Open
Subject Keyword	Aerodynamics Supersonic Flow Turbulent Flow Algorithms Aerodynamic Configurations Finite Difference Theory Computational Grids Grid Generation Mathematics Space Shuttle Orbiters Viscous Flow Hyperbolic Differential Equations Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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