Low-speed wind tunnel tests were conducted of a pressure-tapped wing model tha spanned the test section and was located downstream of a half-wing model that generated a tip vortex. Tests of this perpendicular vortex-airfoil interactions showed that the vortex caused a substantial change in the pressure distribution of the downstream wing and also exhibited a spanwise drift as it passed over the wing. The spanwise drift was in the same direction as the spanwise component of the induced flow at the wing surface, and may be attributed to an image effect, similar to the drifting apart of a wing's trailing vortices as they approach ground. Keywords: Vortices; Airfoils; Wind tunnel tests; Reprints.
Vortex-Airfoil Interaction Tests
1986
6 pages
Report
Keine Angabe
Englisch
Aerodynamics , Airfoils , Downstream flow , Trailing vortices , Drift , Low velocity , Wind tunnel tests , Vortices , Wings , Surfaces , Reprints
Vortex-airfoil interaction tests
AIAA | 1986
|Airfoil interaction with impinging vortex
NTRS | 1984
|Airfoil Interaction with Impinging Vortex
NTIS | 1984
|Airfoil Interaction with an Impinging Vortex
NTIS | 1984
|Isolated airfoil - TIP vortex interaction noise
AIAA | 1974
|