Computation of Transonic Flow About Stores
Abstract
The objective of this program was to derive grid generation and fluid flow algorithms to predict the aerodynamics of aircraft/weapon configurations. Both captive carriage and the launch transient mode were considered in the design of the methods. The numerical grid generation techniques developed were both algebraic, based on transfinite interpolation, and elliptic, based on iterative solution of partial differential equations. The techniques were incorporated into one code that became the numerical grid generation for the Eglin Arbitrary Geometry Implicit Euler (EAGLE) code. In addition, an adaptive version of the grid generation code was developed and applied to missile configurations. The flow solvers developed were all upwind, finite volume schemes ranging from explicit, split-flux vector to implicit, split-flux difference algorithms. Both steady and unsteady, Euler and Navier-Stokes, were written and applied to various configurations. Two implicit algorithms were employed to form the EAGLE flow solver code. This code was run on complex aircraft/weapon configurations, including the launch transient problem of a weapon releasing from an aircraft pylon.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1989
- Accession Number
- ADA210402
Entities
People
- David L. Whitfield
- Joe F. Thompson
Organizations
- Mississippi State University