Improvements in the Formulation and Numerical Solution of the Euler Problem for Swept Wings
Abstract
A multigrid cell-vertex finite volume Euler method has been used to calculate steady inviscid transonic flow past the ONERA M6 wing. The treatment of the far-field boundary conditions includes the effect of velocity perturbations generated from Klunker's analytic asymptotic solution to the transonic small-disturbance equation. The geometry of the wing tip is modelled with three successively finer C-O grids. The results obtained show marked differences in comparison with those obtained on C-H grids. They indicate that a shock-wave mechanism can contribute to the generation of tip vortices in compressible inviscid flow, and that for reliable prediction of wing performance it is important to model well both the wing-tip geometry and the flow around the tip. Keywords: Finite volume; Swept wing; Far-field boundary conditions; Wing tip modelling; Vortex generation; Euler equations; Transonic flow; Boundary value problems; Great Britain.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1988
- Accession Number
- ADA203518
Entities
People
- M. F. Paisley
- M. G. Hall
Organizations
- Royal Aircraft Establishment