Three-Dimensional Transonic Flow Analysis.
Abstract
A computer program was written to calculate the steady, inviscid, transonic flow about an unyawed wing/body configuration. The code is based on the nonconservative form of the full potential equation formulated in global, wing-adapted coordinates that are not surface-conforming. Numerical solution of the governing equations is accomplished via application of type-dependent, rotated finite-difference operators and the method of line relaxation. Exact wing/body surface conditions are enforced by an imaging scheme that involves both surface control points and surface-adjacent computation points. Coordinate stretching permits far-field boundary conditions to be treated exactly; an embedded relaxation scheme computes the downwash field in the Trefftz plane. Present geometric capability includes a quite general wing attached at mid-height to a blunt-nosed, semi-infinite cylinder of varying crossplane radius. Representative solutions computed on a grid of moderate density are presented for a checkout configuration that includes ONERA Wing M6; comparisons with wing-alone experimental data are shown also. Code limitations and modifications required to further develop the program are discussed. A code listing and a user's guide summary are provided. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 30, 1980
- Accession Number
- ADA101944
Entities
People
- Frank W. Spaid
- Gerald E. Chmielewski