Detailed mean flow measurements were obtained at stations up to thirty chordlengths downstream in an airfoil trailing vortex using a yawhead pressure probe in the Virginia Tech Six-Foot Subsonic Tunnel. Mass injection at the wingtip was shown to hasten the vortex decay. A theoretical method has been developed to show the effect of wing circulation distribution on the structure of the outer portion of the vortex and excellent agreement with the experimental data is demonstrated. Experimental results indicate a much slower decay and higher tangential velocities than previously expected.
The farfield structure of aircraft wake turbulence.
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1972 ; San Diego, CA
01.01.1972
Aufsatz (Konferenz)
Keine Angabe
Englisch
The farfield structure of aircraft wake turbulence
AIAA | 1972
|Aircraft Wake Turbulence Avoidance
NTIS | 1971
|Aircraft wake turbulence avoidance
NTRS | 1971
|