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- W2314271286 abstract "A study of the effects of discrete jets, at the blade tips, on tip vortex of a rotor blade has been carried out. Flow measurements and visualizations were conducted on a static rotor test stand. Hot-film measurements in the near wake of a 'hovering' rotor were used to quantitativel y compare velocities associated with tip vortices between a baseline and a modified blade incorporating tip blowing. Results show dramatic reductions in maximum velocities in the near field. Typical reductions are from 0.475Vtip (baseline) to 0.25 Vtip with blowing at Cu = 0.0033. Increased unsteadiness in the near field region of the vortex was observed. Visualization revealed tip blowing reduced the coherence of the modified blade's vortex core. Smoke-flow visualization revealed outward radial movement of the vortex core in the vicinity of the rotor tip, with tip blowing. I. INTRODUCTION The ability to control or modify most flows depends on our ability to control or modify flow vorticies. Much research has been performed to understand the nature of various vortical flows and to determine the relationships between generation, strength, structure, stability, and accelerated decay of vortices 14. One fluid problem that has benefited from such research is flow in concentrated vortices, such as flow over the wing tips. Tip vortices are undesirable by-product of lift generated on 3-D aerodynamic surfaces. These vortices are directly linked to the reduced aerodynamic efficiency of such lifting bodies. This reduction in efficiency is manifested in the induced drag force. Furthermore, interactions of these vortices with other structures result in undesirable noise and structural vibration. Examples of such interactions include noise and vibration from helicopter rotors known as Blade Vortex Interactions (BVI), and large unexpected rolling moments experienced by small aircraft that fly into the wakes of larger aircraft. Obviously, there are good reasons to seek ways to modify or to disperse, and to rapidly attenuate such vortices. In attempting to decrease the vortex strength or to change its stability, the most obvious place to start is to consider mechanisms of vortex decay which occur naturally. There are three known categories of vortex decay. The first is viscous diffusion. This involves the weak means of natural vortex decay which relies upon the effect of shear between fluid particles to slow the rotational velocities of the vortex to the point where they are no longer strong enough to overcome ambient disturbances. Viscous diffusion is generally very slow, due to small viscosity of air, and can take miles to dissipate tip vortices produced by large passenger aircraft assuming other flow instabilities do not accelerate the decay process. The strength and persistence of tip vortices means that this natural mechanism is generally far too slow to be much useful from an engineering standpoint." @default.
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- W2314271286 date "1998-06-02" @default.
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- W2314271286 title "Control of helicopter blade tip vortex" @default.
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- W2314271286 doi "https://doi.org/10.2514/6.1998-2240" @default.
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