Closing Developments in Aerodynamic Simulation with Disjoint Patched Meshes.
Abstract
This research has aimed at providing computational tools and procedures as the building blocks for a system to permit efficient solution and high resolution capture of flow structure in gas dynamic problems of realistically complex geometries. The research yielded a comparatively simple algebraic procedure for constructing two dimensional geometry fitted base level composite meshes in quadrilateral patches. The method provides complete control of coordinate distribution and gradient on all patch boundaries which may include slope discontinuties. A robust upwind implicit method (CSCM) was the basis to solve the two dimensional pseudo time dependent Euler or compressible Navier Strokes equations. Research into solution algorithms for that upwind method yielded a more robust diagonally dominant (DDADI) approximate factorization that subsequently led to a family of rapidly convergent and data storage and management efficient relaxation schemes. Those effectively explicit and unconditionally stable upwind algorithms have led to a simple robust boundary procedure based on interpolation of conservative variable data from other patches over-lying interior patch boundaries where coordinates are discontinuous. Results of preliminary tests with model problems show the desired accuracy and great potential for enhancing engineering productivity. Keywords: Euler equations; Flow fields; Algebraic grid generation; Upwind method; Relaxation; and Approximate factorization.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 24, 1986
- Accession Number
- ADA174958
Entities
People
- Charles K. Lombard