Abstract In the present paper the development of vortex wake starting from the vortex sheet at the trailing edge of a transport aircraft wing up to the far field over 60 spans downstream is investigated. Different configurations of a half model were investigated in wind and water tunnels as well as in a towing tank by hot-wire anemometry and particle image velocimetry. In addition to an understanding of the development of the wake, means for the attenuation of the impact on following aircraft were investigated. A fin was installed on the suction side of the wing to investigate the impact on the vortex system downstream. The possibility of exploiting short-wave cooperative instabilities to accelerate vortex decay were investigated as well. This included active excitation of instabilities via ailerons oscillated in antiphase.
Vortex Sheets of Aircraft in Takeoff and Landing
2010-01-01
23 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Particle Image Velocimetry , Wind Tunnel , Vortex Sheet , Vortex Wake , Vortex System Engineering , Aerospace Technology and Astronautics , Classical Continuum Physics , Engineering Fluid Dynamics , Appl.Mathematics/Computational Methods of Engineering , Fluid- and Aerodynamics , Numerical and Computational Physics
Vortex Sheets of Aircraft in Takeoff and Landing
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