Three-Dimensional Transonic Flow Analysis.
Final scientific rept. 1 May 76-30 Jun 80,
MCDONNELL DOUGLAS RESEARCH LABS ST LOUIS MO
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A computer program was written to calculate the steady, inviscid, transonic flow about an unyawed wingbody 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 wingbody 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 users guide summary are provided. Author
- Computer Programming and Software
- Fluid Mechanics