Numerical simulation of transonic separated flows over low-aspect-ratio wings
Journal of Aircraft, vol.24, no.8, pp.531-539, 1987 (Scopus)
- Publication Type: Article / Article
- Volume: 24 Issue: 8
- Publication Date: 1987
- Doi Number: 10.2514/3.45472
- Journal Name: Journal of Aircraft
- Journal Indexes: Scopus
- Page Numbers: pp.531-539
- Ankara Yıldırım Beyazıt University Affiliated: No
Abstract
Transonic flowfields about a low-aspect-ratio advanced technology wing have been computed using a viscous/inviscid zonal approach. The flowfield near the wing where viscous effects are important was solved using the “Reynolds-averaged Navier-Stokes equations” in “thin-layer” form. The Euler equations were used to determine the flowfield in regions away from the wing where viscous effects are insignificant. A zonal grid using an H-H topology was generated around the wing by first solving a set of Poisson’s equations for the global grid. This grid was then subdivided into separate zones of viscous or inviscid flow as suggested by the flow physics. A series of flow cases were computed and compared with corresponding sets of experimental data. All cases showed good agreement with experiment in terms of the pressure field. Also, an encouraging correlation between computed separated surface flow and experimental oil flow was obtained. © American Institute of Aeronautics and Astronautics, Inc., 1987. All rights reserved.