Abstract
Noise tests using the NASA SR-6 advanced design propeller in the Boeing Transonic Wind Tunnel have recently been completed. Measurements were taken both with and without an acoustically treated test section. A wide range of helical tip speeds and power loadings were explored. Noise test techniques previously not applied to advanced design propeller testing have shown results indicating an increased level of confidence in the measured signatures. Typical results are presented, along with recommendations for future noise tests and elementary empirical prediction methods for the SR-6.
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