Numerical simulation of transonic separated flows over low-aspect ratio wingsTransonic flow fields about a low-aspect-ratio advanced technology wing have been computed using a viscous/inviscid zonal approach. The flow field 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 flow field 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, a good correlation between computed separated surface flow and experimental oil flow was obtained.
Document ID
19860037966
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kaynak, U. (Informatics General Corp. Palo Alto, CA, United States)
Holst, T. L. (NASA Ames Research Center Moffett Field, CA, United States)
Sorenson, R. L. (NASA Ames Research Center Moffett Field, CA, United States)
Cantwell, B. J. (Stanford University CA, United States)