Vortex Breakdown over Slender Delta Wings (Eclatement tourbillonnaire sur les ailes delta effil es)
Abstract
The report contains a study of the phenomenon of leading-edge vortex breakdown over slender delta wings conducted by the NATO/RTO/AVT Task Group AVT-080. After an introduction and discussion of highlights, a chapter is devoted to a critical assessment of available experimental studies of the vortex breakdown phenomenon. Eight reliable experimental data sets are collected and compiled. These data sets are described in separate chapters and were obtained on more or less identical delta wing models tested in different wind tunnel test facilities. The datasets include timeaverage results at static model conditions, ensemble-average results at dynamic model conditions and unsteady results at static/dynamic model conditions. Based on the critical assessment, a benchmark test case is selected that provides sufficiently reliable data for validation of the numerical predictions. In separate chapters ten state-of-the-art numerical solutions from various research institutes are described that have been obtained for the benchmark test case configuration and test conditions. Studies of the effects of parameters like grid density, turbulence modeling, time scaling, etc., have been performed. In addition, for a special delta wing configuration, the effects of tunnel wall interference and of interactions between vortices have been calculated. In the final three chapters advanced analytical methods are described. The report is of great value to scientists involved in the development of design methods for military aircraft configurations, but also for high speed civil and/or space aircraft.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 2009
- Accession Number
- ADA531207
Entities
Organizations
- NATO Science and Technology Organization