Visualization and Anemometry of Forced Unsteady Flows About an X-29 Model
Abstract
Numerous investigations on forced unsteady flows and associated lift enhancements suggest significant aerodynamic utility. To demonstrate the application potential of unsteady flow technology, and investigation comparing flow visualization and hotwire velocity measurements of the flow about an X-29 aircraft model was accomplished. Precious flow visualization has qualitatively defined the flow structures, and comparisons with quantitatively defined the flow structures, and comparisons with quantitative hotwire anemometry data provides insight into the aerodynamic enhancement of these forced unsteady flows. Flow visualization shows intricate interactions between the wingtip and leading edge vortices on the surface of the canard. These structures convect downstream and influence the flow patterns about the wing. Hotwire velocity measurements were taken above and below the wing, adding a quantitative dimension to understanding these flows. The unsteady flow phenomena show significant benefits that can be used to enhance the aerodynamic agility of maneuvering aircraft. (jd)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 06, 1988
- Accession Number
- ADA228101
Entities
People
- J. Ashworth
- M. Luttges
- T. Mouch
Organizations
- Air Force Research Laboratory