NTRS - NASA Technical Reports Server

Back to Results
Surface grid generation for wing-fuselage bodiesIn the application of finite-difference methods to obtain numerical solutions of viscous compressible fluid flow about wing-fuselage bodies, it is advantageous to transform the governing equations to an idealized boundary-fitted coordinate system. The advantages are reduced computational complexity and added accuracy in the application of boundary conditions. The solution process requires that a grid be superimposed on the physical solution domain which corresponds to a uniform grid on a rectangular computational domain (uniform rectangular parallel-epiped). Grid generation is the determination of a one to one relationship between grid points in the physical domain and grid points in the computational domain. A technique for computing wing-fuselage surface grids using the Harris geometry and software for smooth-surface representation is described. Grid spacing control concepts which govern the relationship between the wing-fuselage surface and the computational grid are also presented.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Smith, R. E.
(NASA Langley Research Center Hampton, VA, United States)
Kudlinski, R. A.
(NASA Langley Research Center Hampton, VA, United States)
Pitts, J. I.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
March 1, 1984
Publication Information
Publication: Computer-Aided Geometry Modeling
Subject Category
Numerical Analysis
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.
Document Inquiry

Available Downloads

There are no available downloads for this record.
No Preview Available