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- W2119132901 abstract "An experimental investigation was conducted in the UARL Acoustic Research Tunnel to define the characteristics associated with the interaction of a stationary tip vortex and a downstream stationary airfoil. This model test geometry simulated, in its simplest form, the tip vortexblade interaction which occurs on single rotor helicopters during hover. For moderate to high lift test conditions, the vortex-airfoil interaction was found to cause local blade stall with an attendant increase in the blade far-field noise. These results indicated that this interaction may be an important source of helicopter broadband during hover. Cross-correlation measurements conducted amongst surface-mounted and far-field microphones demonstrated that the operative mechanism was edge noise arising from the interaction of stall generated eddies with the airfoil trailing edge. This mechanism would be expected to be responsible for increased at stall conditions in other, nonrotary wing, applications." @default.
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- W2119132901 date "1975-01-01" @default.
- W2119132901 modified "2023-10-17" @default.
- W2119132901 title "Isolated Airfoil-Tip Vortex Interaction Noise" @default.
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- W2119132901 doi "https://doi.org/10.2514/3.59798" @default.
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