It has long been thought by many that separated flows violated the assumptions of integral boundary-layer methods coupled to inviscid flow solvers. In this paper, it is shown how to extend the transpiration theory of the equivalent inviscid flow to essentially arbitrary large separation regions. It is shown through computational examples that integral boundary-layer methods can indeed give useful results up to stall in some situations. The limitations of these methods are also discussed and compared to Reynolds-averaged Navier–Stokes methods.
Implementation of a Separated Flow Capability in TRANAIR
AIAA Journal ; 52 , 8 ; 1699-1716
2014-03-20
18 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
CST Transonic Optimization Using Tranair++
AIAA | 2008
|TRANAIR applications to fighter configurations
AIAA | 1989
|CST Transonic Optimization Using Tranair++
British Library Conference Proceedings | 2008
|TRANAIR applications to engine/airframe integration
AIAA | 1989
|TRANAIR applications to engine/airframe integration
AIAA | 1990
|