Abstract
A wind-tunnel investigation was conducted to determine the nature, strength, and variation with airspeed of the acoustic sources of the augmentor wing propulsive-lift concept. The augmentor wing overall noise is dominated by the high-frequency jet mixing noise characteristic of the lobed primary nozzle. The augmentor modifies the intensity and propagation characteristics of the jet sources, especially those that exist inside the augmentor. The interaction of the turbulent flow with the augmentor creates flow-frequency, low-intensity surface noise and trailing-edge noise. These sources dominate any jet mixing noise that is present at the low frequencies and could become significant if the jet noise were suppressed by treating the augmentor with a lining tuned to the jet noise source location. The far-field noise of the untreated augmentor is unaffected by airspeed; however, this may not be the case when the jet noise is suppressed, because the trailing-edge surface pressure and correlations with far-field noise do show a reduction with forward speed.
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